Patent Assignment
Reel/Frame 046479/0807
Change of Name
Recorded: 2018-05-23
Pages: 60
Assignor
SNECMA
Executed: 2016-08-03
Assignee
SAFRAN AIRCRAFT ENGINES
2 BOULEVARD DU GÉNÉRAL MARTIAL VALIN, 75015 PARIS, FRANCE
Covered Properties
(2200)
Process for Making a Composite Rotor with Metallic Matrix
Patent:
5,745,994 →
Application:
08/747,765 →
Device for Separating and Filtering Particles in a Flow of Fluid
Patent:
5,653,880 →
Application:
08/757,952 →
Pivoting Vane Internal Extremity Bearing
Patent:
5,796,199 →
Application:
08/759,927 →
Oil Separator Rotor for Lubrication Enclosure
Patent:
5,776,229 →
Application:
08/764,450 →
Cooling Device for a Turboshaft Engine on an Aircraft
Patent:
5,806,793 →
Application:
08/766,472 →
Cooled Turbine Guide Vane
Patent:
5,772,398 →
Application:
08/774,636 →
Method and Apparatus for the Serial Production of Parts by Electrochemical Machining
Patent:
5,900,134 →
Application:
08/775,747 →
Turbine Disk Cooling Device
Patent:
5,800,125 →
Application:
08/779,438 →
Drill Bit Having a Hemispherical Head with an Evolutive Cut
Patent:
5,725,338 →
Application:
08/780,233 →
Movable Fan Vane with a Safety Profile
Patent:
5,853,286 →
Application:
08/781,838 →
Labyrinth Disk with Built-in Stiffener for Turbomachine Rotor
Patent:
5,816,776 →
Application:
08/791,051 →
Thermal Barrier Coating with Improved Sub-Layer and Parts Coated with Said Thermal Barrier
Patent:
5,843,585 →
Application:
08/807,755 →
Method of Producing a Coating Layer on a Localized Area of a Superalloy Component
Patent:
5,890,274 →
Application:
08/816,738 →
Restraining Device for the Root of a Fan Blade
Patent:
5,820,347 →
Application:
08/818,941 →
Fuel Injection Supply Circuit for Providing a Metered Decontaminated Flow of Fuel to the Fuel Injectors
Patent:
5,832,717 →
Application:
08/819,370 →
Bypass Engine with Means for Limiting Gas Leakage
Patent:
5,822,975 →
Application:
08/834,877 →
Tools for Mounting a Turbo Aero Engine Distributor
Patent:
5,918,356 →
Application:
08/840,852 →
Gas Turbine Engine Combustion Chamber for Optimizing the Mixture of Burned Gases
Patent:
5,934,067 →
Application:
08/845,133 →
Process for Manufacturing a Hollow Turbomachine Blade and a Multiple-Action Furnace Press for Use in Said Process
Patent:
5,933,951 →
Application:
08/871,637 →
Laser-Assisted Milling Process
Patent:
5,906,459 →
Application:
08/873,082 →
Method for Enabling Operation of an Aircraft Turbo-Engine with Rotor Unbalance
Patent:
5,974,782 →
Application:
08/873,452 →
Variable Geometry Turbojet Engine Exhaust Nozzle
Patent:
5,934,564 →
Application:
08/874,507 →
Gas Containment Box Used with a Welding Head
Patent:
5,950,904 →
Application:
08/877,557 →
Reduced Pollution Combustion Chamber Having an Annular Fuel Injector
Patent:
5,937,653 →
Application:
08/884,668 →
Deburring Tool and Process on a Hole Opposite the Tool
Patent:
5,897,273 →
Application:
08/891,028 →
Layout and Process for Adjusting the Diameter of a Stator Ring
Patent:
5,915,919 →
Application:
08/893,521 →
Process for the Manufacture of a Hollow Turbomachine Blade and Apparatus for Use in Said Process
Patent:
5,946,802 →
Application:
08/909,874 →
Truing Wheel with Incorporated Cooling
Patent:
5,846,125 →
Application:
08/911,043 →
Fuel Injection System with Improved Air/Fuel Homogenization
Patent:
5,941,075 →
Application:
08/912,815 →
Process for Manufacturing a Hollow Turbomachine Blade and Progressive Hot Twisting Apparatus for Use in Said Process
Patent:
5,933,952 →
Application:
08/914,186 →
Aerodynamic Fuel Injection System for a Gas Turbine Engine
Patent:
6,035,645 →
Application:
08/939,084 →
Oxidizer Control Device for a Gas Turbine Engine
Patent:
5,996,333 →
Application:
08/950,017 →
Method of Manufacturing a Hollow Blade for a Turbomachine
Patent:
5,896,658 →
Application:
08/951,292 →
Fibre-Reinforced Rotor Stage for a Turbomachine
Patent:
5,941,688 →
Application:
08/964,632 →
Inert Gas Electric Arc Welding Process and Torch for Use Therein
Patent:
5,965,037 →
Application:
08/968,451 →
Redundant Front Suspension System for a Turboshaft Engine
Patent:
5,871,175 →
Application:
08/974,423 →
Redundant Front Suspension System for a Turboshaft Engine
Patent:
5,871,176 →
Application:
08/974,559 →
Redundant Front Suspension System for a Turboshaft Engine
Patent:
5,871,177 →
Application:
08/974,678 →
Process for Producing a Coating for Providing Superalloys with Highly Efficient Protection Against High-Temperature Corrosion, a Protective Coating Formed by the Process, and Articles Protected by the Coating
Patent:
6,183,888 →
Application:
08/989,059 →
Non-Destructive Process for Estimating the Ageing of an Article Made of a Composite Material
Patent:
5,922,957 →
Application:
09/000,976 →
Noise-Absorption Structures and Walls Constituted Thereby
Patent:
6,332,027 →
Application:
09/003,900 →
Control of Cooling Flows for High-Temperature Combustion Chambers
Patent:
6,105,371 →
Application:
09/006,955 →
Cooling System for Turbine Blade Platforms
Patent:
6,017,189 →
Application:
09/013,238 →
Linked Multilayer Fabric for Structural Composite Materials
Patent:
5,899,241 →
Application:
09/018,176 →
Thrust Reverser for a High Bypass Turbofan Engine
Patent:
6,050,522 →
Application:
09/022,277 →
Method of Bladder Moulding Thin Articles Made of a Composite Material Using a Conforming Device
Patent:
6,083,448 →
Application:
09/027,222 →
Process for Producing Precision Hollow Articles Made of Composite Material
Patent:
6,290,889 →
Application:
09/035,299 →
A Constant-Speed Twin Spool Turboprop Unit
Patent:
6,082,967 →
Application:
09/047,403 →
Drive System for a Propeller Driven Transport Aircraft
Patent:
6,279,852 →
Application:
09/061,092 →
System for the Admission of Air into a Working Section of a Gas Turbine Engine
Patent:
6,082,669 →
Application:
09/071,157 →
Protective Coating for Metal Components Providing Good Corrosion Resistance in a Saline Atmosphere, and Method of Producing Said Coating
Patent:
5,989,735 →
Application:
09/080,238 →
Turbine Vane Cooling System
Patent:
5,993,156 →
Application:
09/104,200 →
Apparatus for Heating or Cooling a Circular Housing
Patent:
6,035,929 →
Application:
09/115,523 →
Apparatus for Ventilating a Turbine Stator Ring
Patent:
5,964,575 →
Application:
09/115,695 →
Process for the Assembly or Refacing of Titanium Aluminide Articles by Diffusion Brazing
Patent:
6,223,976 →
Application:
09/154,513 →
Method of Improving Oxidation and Corrosion Resistance of a Superalloy Article, and a Superalloy Article Obtained by the Method
Patent:
6,228,513 →
Application:
09/158,094 →
Turbomachine Combustion Chamber
Patent:
6,070,412 →
Application:
09/179,896 →
Cooled Turbine-Nozzle Vane
Patent:
6,109,867 →
Application:
09/199,777 →
Process for Manufacturing a Hollow Turbomachine Blade and a Multiple-Action Furnace Press for Use in Said Process
Patent:
6,210,630 →
Application:
09/204,155 →
Self-Washing Device for Separating and Filtering Solid Particles from a Flow of Liquid , and Use of the Device in a Fuel Injection Circuit
Patent:
6,125,826 →
Application:
09/212,864 →
Titanium-Based Intermetallic Alloys
Patent:
6,132,526 →
Application:
09/213,247 →
Redundant Regulation Valve
Patent:
6,223,774 →
Application:
09/221,941 →
Turbomachine with Mutual Braking of C0NCENTRIC Shafts
Patent:
6,135,712 →
Application:
09/227,879 →
Apparatus for Controlling the Radial Play of a Roller Bearing
Patent:
6,261,003 →
Application:
09/244,639 →
Circular Stage of Vanes Connected at Internal Ends Thereof by a Connecting Ring
Patent:
6,129,512 →
Application:
09/252,821 →
Soundproofing Panel and Method of Producing Said Panel
Patent:
6,085,865 →
Application:
09/257,191 →
Method and Device for Reversing the Thrust of Very High Bypass Ratio Turbojet Engines
Patent:
6,148,605 →
Application:
09/262,345 →
Method of Manufacturing a High Heat Flux Regenerative Circuit, in Particular for the Combustion Chamber of a Rocket Engine
Patent:
6,209,199 →
Application:
09/271,394 →
Method of Reducing the Gap Between a Liner and a Turbine Distributor of a Turbojet Engine
Patent:
6,163,959 →
Application:
09/272,774 →
Method for Manufacturing a Ceramic Composite Material
Patent:
6,251,317 →
Application:
09/284,221 →
Progressive Hot Twisting Apparatus for Use in a Process for Manufacturing a Hollow Turbomachine Blade
Patent:
6,242,715 →
Application:
09/290,996 →
Ultrasonic Testing Method for a Part of Complex Geometry
Patent:
6,202,489 →
Application:
09/302,374 →
Ceramic Heat Barrier Coating Having Low Thermal Conductivity, and Process for the Deposition of Said Coating
Patent:
6,251,504 →
Application:
09/325,042 →
High-Pressure Turbine Stator Ring for a Turbine Engine
Patent:
6,200,091 →
Application:
09/330,063 →
Particle Traps for Turbo-Prop Engine
Patent:
6,129,509 →
Application:
09/342,730 →
Converging Exhaust Nozzle Fitted with Translating Cold Flaps
Patent:
6,164,563 →
Application:
09/356,321 →
Turbo Jet Engine Exhaust Nozzle with Masked Gas Jet
Patent:
6,179,225 →
Application:
09/356,362 →
Method and Device for Machining Holes or Shapes of Varying Profile Using an Excimer Laser
Patent:
6,329,632 →
Application:
09/359,811 →
Sealing Arrangement with Automatic Clearance Adjustment
Patent:
6,338,490 →
Application:
09/363,838 →
Closed Electron Drift Plasma Thruster Adapted to High Thermal Loads
Patent:
6,281,622 →
Application:
09/378,795 →
Method for Metal Coating of Fibres by Liquid Process
Patent:
6,174,570 →
Application:
09/381,296 →
Low Thermal Conductivity Heat Barrier Coating, a Metal Article Having Such a Coating, and a Process for Depositing the Coating
Patent:
6,312,832 →
Application:
09/391,342 →
Cooled Turbine Blade
Patent:
6,328,531 →
Application:
09/412,759 →
Process and Instrument for Checking the Bonding of the Cellular Core of a Honeycomb to a Skin
Patent:
6,452,670 →
Application:
09/429,306 →
Process for the Manufacture of Thin Ceramic Cores for Use in Precision Casting
Patent:
6,286,582 →
Application:
09/436,770 →
Dual-Contact Brush Seal
Patent:
6,328,311 →
Application:
09/453,511 →
Closed Electron Drift Plasma Thruster with a Steerable Thrust Vector
Patent:
6,279,314 →
Application:
09/474,546 →
Cooling System for a Turbomachine Speed Reducer
Patent:
6,282,881 →
Application:
09/476,083 →
Turbojet Engine Thrust Reverser and Exhaust Nozzle
Patent:
6,289,670 →
Application:
09/479,077 →
Fuel circuit with protected main filter
Patent:
6,251,270 →
Application:
09/481,382 →
Turbojet engine thrust reverser and exhaust nozzle assembly
Patent:
6,185,926 →
Application:
09/497,178 →
Turbomachine including a device for supplying pressurized gas
Patent:
6,334,755 →
Application:
09/506,685 →
Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle
Patent:
6,276,126 →
Application:
09/523,465 →
Self-Testable Architecture for Overspeed Limitation and Cutoff Systems When the Turbojet Stops Description
Patent:
6,393,353 →
Application:
09/527,831 →
Process for the Detection of Damage to Components of an Engine
Patent:
6,389,887 →
Application:
09/532,900 →
Swiveling, Converging-Diverging, Axisymmetric Exhaust Nozzle
Patent:
6,375,095 →
Application:
09/549,539 →
Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring
Patent:
6,360,527 →
Application:
09/550,024 →
Universal-joint vectoring system for a turbojet-engine exhaust nozzle
Patent:
6,327,846 →
Application:
09/551,749 →
Retaining Arrangement for a Bearing, in Particular for a High Pressure Compressor Shaft
Patent:
6,338,578 →
Application:
09/554,516 →
Method for Obtaining Thin, Light and Rigid Metal Parts
Patent:
6,379,480 →
Application:
09/581,183 →
Method of Manufacturing Self-Soldering Shaped Pieces by Powder Metallurgy
Patent:
6,391,252 →
Application:
09/581,529 →
Thrust Reverser with Mutually Configurable Baffles
Patent:
6,256,980 →
Application:
09/581,542 →
Direct Control Fuel Valve for Fuel Flow Injecting Circuit
Patent:
6,367,768 →
Application:
09/582,226 →
High-Pressure Compressor Stator
Patent:
6,390,771 →
Application:
09/586,791 →
Protection device for protecting control mechanism of inlet guide-vanes of turbojet engine
Patent:
6,398,483 →
Application:
09/589,806 →
Radiographic Control of an Object Having a Crystal Lattice
Patent:
6,295,335 →
Application:
09/600,872 →
Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle
Patent:
6,349,539 →
Application:
09/613,733 →
Method and a system for putting a space vehicle into orbit, using thrusters of high specific impulse
Patent:
6,213,432 →
Application:
09/619,281 →
Turbine Vane with Enhanced Profile
Patent:
6,428,281 →
Application:
09/624,486 →
Suspension System with Intrinsic Safety Features for Aircraft Powerplants
Patent:
6,474,596 →
Application:
09/678,259 →
Method of Manufacturing a High Heat Flux Regenerative Circuit, in Particular for the Combustion Chamber of a Rocket Engine
Patent:
6,516,872 →
Application:
09/711,186 →
Method and machine for the ultrasonic peening of parts on a wheel
Patent:
6,336,844 →
Application:
09/714,194 →
Method for the ultrasonic peening of large sized annular surfaces of thin parts
Patent:
6,289,705 →
Application:
09/714,223 →
Method of improving oxidation and corrosion resistance of a superalloy article, and a superalloy article obtained by the method
Configuration for Axial Retention of Blades in a Disc
Ceramic Heat Barrier Coating Having Low Thermal Conductivity, and Process for the Deposition of Said Coating
Method for the Early Detection of Aerodynamic Instabilities in a Turbomachine Compressor
Device and Process for Controlling the Pressure and Delivery of a Fuel Feed to a Servovalve Unit
Device for Fixing a Turbine Ferrule
Patent:
6,575,697 →
Application:
09/868,902 →
Blade Locking Device with Hammer Fastener on a Disk
System for Ventilating a Pair of Juxtaposed Vane Platforms
Patent:
6,457,935 →
Application:
09/883,948 →
Rotor Blade Retaining Apparatus
Hydromechanical System for Limiting Excess Engine Speed
Arrangement for Adjusting the Diameter of a Gas Turbine Stator
Patent:
6,666,645 →
Application:
09/926,122 →
Method for Measuring Adherence of a Coating on a Substrate
Method of Revealing Structure for Single-Crystal Superalloys
Formation of an Aluminide Coating, Incorporating a Reactive Element, on a Metal Substrate
Device for Controlling Variable-Pitch Blades
Self-Cleaning Metering Device
Process and Device for Attenuating the Noise Made in a Turbomachine by Rotor/Stator Interaction
Method of Making a Protective Coating Forming a Thermal Barrier with a Bonding Underlayer on a Superalloy Substrate, and a Part Obtained Thereby
Acoustic Inspection of One-Piece Bladed Wheels
Linking Arrangement of a Turbine Stator Ring to a Support Strut
Device and Process for Economizing Fuel Supply in a Fuel Supply Circuit
Stator Ring Ventilation Assembly
Method and Apparatus for Peening Tops of Cooled Blades
Method and Apparatus for Ultrasonic Peening of Annular Recesses for the Attachment of Blades to a Rotor
Method and Apparatus for Ultrasonic Peening of Axial Recesses for the Attachment of Blades to a Rotor
Method for Extending the Life of Attachments That Attach Blades to a Rotor
Full Cooling of Main Injectors in a Two-Headed Combustion Chamber
Fuel Injector with an Optimized Metering Device
Method of Assembling a Fuel Injector for the Combustion Chamber of a Turbomachine
Internal Stator Shroud
Patent:
6,679,679 →
Application:
09/993,602 →
Assembly Formed by at Least One Blade and a Blade-Fixing Platform for a Turbomachine, and a Method of Manufacturing It
Blade Maintenance Tool, and Its Application to Friction Welding of Blades
Turbomachine Stator Flap, and a Method of Manufacturing It
Two-Level Pressurization Valve Controlled by a Fuel Metering Unit
Installation for Shaping a Part and Application to Hot Forming
Play Measuring Sensor by Multiple Depth Abrasion
Sealable Casing Having a Quarter-Turn Closing Arrangement
Bleed System Driven in Simplified Manner for a Turbojet or Turboprop Engine
Lubrication Cutoff Device
Transverse Ultrasound Peening of Blades on a Rotor
Fuel Metering Unit with Two Integrated Outlet Ports
Centripetal Air-Bleed System
Turbomachine Rotor Assembly with Two Bladed-Discs Separated by a Spacer
Fixing Metal Caps Onto Walls of a Cmc Combustion Chamber in a Turbomachine
Combustion Chamber Provided with a System for Fixing the Chamber End Wall
Connection for a Two-Part Cmc Chamber
Fastening a Cmc Combustion Chamber in a Turbomachine Using the Dilution Holes
Mounting for a Cmc Combustion Chamber of a Turbomachine by Means of Flexible Connecting Sleeves
Resilient Mount for a Cmc Combustion Chamber of a Turbomachine in a Metal Casing
Architecture for a Combustion Chamber Made of Ceramic Matrix Material
Fastening a Cmc Combustion Chamber in a Turbomachine Using Brazed Tabs
Variable Cycle Propulsion System with Compressed Air Tapping for a Supersonic Airplane
Variable Cycle Propulsion System with Gas Tapping for a Supersonic Airplane
Variable Cycle Propulsion System with Mechanical Transmission for a Supersonic Airplane
Emergency Device for Relighting a Windmilling Turbojet
Bladed Rotor Disc Side-Plate and Corresponding Arrangement
Aeromechanical Injection System with a Primary Anti-Return Swirler
Stay Sector of Stator Shroud of the High-Pressure Turbine of a Gas Turbine Engine with Clearance Control
Method of Manufacturing an Integral Rotor Blade Disk and Corresponding Disk
Compressor Air Drawing Off System
Gas Turbine Blade Cooling Circuits
Cooling Circuits for a Gas Turbine Blade
Jet Engine Suspension
Electrohydraulic Device for Varying the Pitch of the Blades of a Machine Rotor
Electrohydraulic Actuator
Fixed Guide Vane Assembly Separated into Sectors for a Turbomachine Compressor
Bleed-Off Device in a Bypass Turbojet
Abradable Coating for Gas Turbine Walls
Fuel Metering Device for a Turbomachine Injector
Turbomachine Injectors
Device for Immobilizing Blades in a Slot of a Disk
Fuel Injection System with Multipoint Feed
High-Temperature Behavior of the Trailing Edge of a High Pressure Turbine Blade
Nozzle-Vane Band for a Gas Turbine Engine
Method for Measuring a Wall Thickness of a Hollow Vane
Device for Straightening the Flow of Air Fed to a Centripetal Bleed in a Compressor
Axial Compressor Disk for a Turbomachine with Centripetal Air Bleed
Turbomachine Rotor Arrangement
Diffuser for Terrestrial or Aviation Gas Turbine
Cooling System for a Gas Turbine Engine Post-Combustion Jet Nozzle
Device for Controlling a Variable-Angle Vane via a Slack-Free Connection
Device for Controlling a Variable-Angle Vane via a Pinch Connection
Stator Blade Pivoting Arrangement in a Turbomachine
Thin Parts Made of Beta or Quasi-Beta Titanium Alloys; Manufacture by Forging
Multimode System for Injecting an Air/Fuel Mixture into a Combustion Chamber
Device for Supporting and Recentering the Shaft of a Turbojet Fan After Uncoupling
Device for Centering a Tube in a Turbine Shaft
Method of Forming a Ceramic Coating on a Substrate by Electron-Beam Physical Vapor Deposition
Dry Self-Lubricating Dense Material; a Mechanical Part Formed from Said Material; a Method of Manufacturing Said Material
Cooling the Upstream End Plate of a High Pressure Turbine by Means of a System of Dual Injectors at the End of the Combustion Chamber
Suspension Part of a Turbojet Engine
Method of Making a Protective Coating Forming a Thermal Barrier with a Bonding Underlayer on a Superalloy Substrate, and a Part Obtained Thereby
Combustion Chamber Sealing Ring, and a Combustion Chamber Including Such a Ring
Metallic Material That Can Be Worn Away by Abrasion; Parts, Casings, and a Process for Producing Said Material
Oil-Damped Sealed Rolling Bearing
Blade for a Turbine Comprising a Cooling Air Deflector
Arrangement for mounting two coaxial shaftlines
Application:
10/476,372 →
Publication:
US 2005/0100258
Structure Comprising a Rotor and Fixed Perturbation Sources and Method for Reducing Vibrations in Said Structure
Turbine Blade with Sealing Element
Gas Turbine Stator Housing
Assembly of Sectors of a Dispensing Unit in a Gas Turbine
Welding Unit with Miniaturised Laser Beam
Method of Locally Repairing Parts Covered with a Thermal Barrier
Gasket with Two Concentric Lips
Device for Maintaining Joints with Sealing Leaves
Device for Stopping in Rotation a Fixed Blade Bearing Sector in a Gas Turbine Casing
Gas Turbine Stator
Fan Blade with Embrittled Tip
Breakable Coupling System for a Turbojet Fan Shaft
Method for the Production of Parts by Means of Diffusion Bonding and Superplastic Forming, and Mold for Carrying Out Said Method
Thermal Spraying Instrument
Thermal Spraying Instrument
Thermal Projection Device
Thermal Projection Device
Gas Turbine with Stator Shround in the Cavity Beneath the Chamber
Fusible Link Comprising Damper and Backstop
Control of Leak Zone Under Blade Platform
Machine Stator and Mounting and Dismounting Methods
Restraining Device for Fan Blade Root
Rotor Recentering After Decoupling
Reinforced Composite Mechanical Component, and Method for Making Same
Annular Combustion Chamber for a Turbomachine
Air Input Device for a Turboprop Engine
Cooling Circuit for Gas Turbine Fixed Ring
Method of Distributing Rotor Blades in a Turbomachine
Cryogenic Rotary Coupling, and Use Thereof in Particular in Articulated Fluid Feed Lines, and in Cryogenic Propellant Rocket Engines
Assistance and Emergency Drive for Electrically-Driven Accessories
Integrated Starter/Generator for a Turbomachine
Controlling the Axial Position of a Fan Blade
Fracturing Different Levels Within a Completion Interval of a Well
Tension Decoupler Device
Drum, in Particular a Drum Forming a Turbomachine Rotor, a Compressor, and a Turboshaft Engine Including Such a Drum
Oil-Damped Rolling Bearing
Casing, a Compressor, a Turbine, and a Combustion Turbine Engine Including Such a Casing
Appliance for Reading Identification Connectors
Fuel Metering Unit with a Compensated Regulator Valve in a Turbomachine
Single-Pass Laser Welding Method of a T Assembly of Metallic Parts
Method of Replacing an Abradable Portion on the Casing on a Turbojet Fan
Powder Material for an Abradable Seal
Method of Making a Coating on a Metal Substrate and/or an Article, Such a Coating, Such a Metal Substrate and/or an Article, and a Cam Forming Such an Article
Retaining Device for a Connection Device, Decoupling System Equipped with Such a Device
System for Retaining an Annular Plate Against a Radial Face of a Disk
Ventilation Device for a High Pressure Turbine Rotor of a Turbomachine
Backswept Turbojet Blade
Turbine Vane Cooled by a Reduced Cooling Air Leak
Turbomachine Turbines with Blade Inserts Having Resonant Frequencies That Are Adjusted to Be Different, and a Method of Adjusting the Resonant Frequency of a Turbine Blade Insert
Device for Cooling Turbine Disks
Annular Platform for a Nozzle of a Low-Pressure Turbine of a Turbomachine
Turboprop Carrier Structure and an Assembly Including Such a Carrier Structure
Turbomachine with Cooled Ring Segments
Device for Injecting Cooling Air into a Turbine Rotor
Assembly for the Manufacture of a Hollow Mechanical Part by Diffusion Bonding and Superplastic Forming, Use of Such an Assembly and Process for Manufacturing Such a Mechanical Part
Wrench with Controlled Tightening
Lightened Turbomachine Blade and Its Manufacturing Process
Nozzle Vane with Two Slopes
Device and Process for Profile Measurement
Method of Fabricating a Hollow Mechanical Part by Diffusion Welding and Superplastic Forming
Process for Forming a Protective Coating Containing Aluminium and Zirconium on a Metal
Graphical Interface System for Manipulating a Virtual Dummy
Device for Controlling Variable-Pitch Vanes in a Turbomachine
Reducing Clearance in a Gas Turbine
Optimizing Ergonomic Movement of a Virtual Dummy
Control Lever Attachment with Play Compensation for Blades with Variable Setting Angles
Rear Fastening Device for Aircraft Engine
Method of Guiding a Blade Having a Variable Pitch Angle
Aircraft Engine Rear Suspension with Thrust Recovery
Front Fastening Device for Aircraft Engine
Combustion Chamber Having a Flexible Connexion Between a Chamber End Wall and a Chamber Side Wall
Process for Obtaining a Flexible/Adaptive Thermal Barrier
Method of Manufacturing a Hollow Blade for a Turbine Engine
System for Sealing the Secondary Flow at the Inlet to a Nozzle of a Turbomachine Having a Post-Combustion Chamber
Long Life Nozzle Flap for Aircraft Turbojets
Turbomachine Nozzle with Noise Reduction
Retention Capacity of a Blade Having an Asymmetrical Hammerhead Fastener, with the Help of Platform Stiffeners
Turbomachine Annular Combustion Chamber
Link Between Two Mechanical Members
Variable Pitch Device for Two Blade Stages Fixed Onto a Turbojet
Plug Sealing Device That Is Not Welded to the Chamber Wall
Arrangement of Bearing Supports for the Rotating Shaft of an Aircraft Engine and an Aircraft Engine Fitted with Such an Arrangement
Screw and Nut Fastening Device
Ventilation Channels in an Afterburner Chamber Confluence Sheet
Aircraft Engine Rear Mount with Thrust Links and Boomerang-Shaped Lever
Device for Maintaining and Positioning Harnesses on a Turbo-Jet Engine
Nozzle Ring with Adhesive Bonded Blading for Aircraft Engine Compressor
Perfected Device for Securing an Engine Shaft on a Bearing Support
Cooled Gas Turbine Blades
Retention Capacity of Blade Having an Asymmetrical Hammerhead Connection
Apparatus for Searching for and Detecting Defects in Parts by Endoscopy
Locking the Cowl Doors of a Turbojet
De-Icing Device for Turbojet Inlet Guide Wheel Vane, Vane Provided with Such a De-Icing Device, and Aircraft Engine Equipped with Such Vanes
Connection Between Bladed Discs on the Rotor Line of a Compressor
Flexible Flap for a Variable-Section Turbomachine Nozzle
Device for Passive Control of the Thermal Expansion of the Extension Casing of a Turbo-Jet Engine
Device for Pivotally Guiding Variable-Pitch Vanes in a Turbomachine
Device for Reducing the Jet Noise of a Turbomachine
Plasma Accelerator with Closed Electron Drift
Guide System for the Outer Pivot of a Variable Stator Vane, for a Turbojet Stator
System and method for managing machine servicing including workscope generation
Application:
10/887,928 →
Publication:
US 2006/0010152
Method of Forming a Ceramic Coating on a Substrate by Electron-Beam Physical Vapor Deposition
Valve Device Having a Long Adjustment Stroke
Holding System for a Rotor End Plate
Inter-Vane Platform with Lateral Deflection for a Vane Support of a Turbine Engine
Lightened Interblade Platform for a Turbojet Blade Support Disc
Cooling Circuits for a Gas Turbine Blade
Device for Controlling Clearance in a Gas Turbine
Afterburner Arrangement
Heat Exchanger on a Turbine Cooling Circuit
Hollow Rotor Blade for the Turbine of a Gas Turbine Engine
Low-Pressure Turbine of a Turbomachine
Device for Estimating the Mass Flow of Fuel
Thermal Barrier Composition and a Ceramic Coating Having Such a Composition
Turbomachine with Low Noise Emissions for Aircraft
Convergent-Divergent Turbojet Nozzle
Cooled Gas Turbine Engine Vane
Air/Fuel Injection System Having Cold Plasma Generating Means
Rotation-Locking of Sectors of Rectifier Blades by Bars in the Parting Planes of the Housing
Provision of Sealing for the Cabin-Air Bleed Cavity Using a Segment Seal
Provision of Sealing for the Cabin-Air Bleed Cavity of a Jet Engine Using Strip-Type Seals Acting in Two Directions
Process for Manufacturing or Repairing a Monobloc Bladed Disc
Turbine Wheel for Turbomachine and the Assembly Method for Such a Wheel
Provision of sealing for the cabin-air bleed cavity of a jet engine using a brush seal
Application:
10/938,571 →
Publication:
US 2005/0102994
Provision of Sealing in a Jet Engine for Bleeding Air to the Cabin Using a Tube with a Double Ball Joint
Turobjet Axisymmetric Nozzle Controlled Hot Flap Shutter
Ventilation System for a Convergent Divergent Exhaust Nozzle
Turboshaft Engine Comprising Two Elements Connected to Each Other with the Interposition of a Seal
Target for Vaporizing Under an Electron Beam, a Method of Fabricating It, a Thermal Barrier and a Coating Obtained from a Target, and a Mechanical Part Including Such a Coating
Arrangement for the Attachment of Distributor Sectors Supporting Vanes Around an Arc of a Circle
Process for Repairing Metallic Pieces Especially Turbine Blades of a Gas Turbine Motor
Endoscope with Deflected Distal Viewing
Ceramic Bit for High Speed Drilling
Device for Attaching a Moving Blade to a Turbine Rotor Disk in a Turbomachine
Automated Polishing Process for Mechanical Parts in Titanium or Titanium Alloy
Turbomachine Blade, in Particular a Fan Blade, and Its Method of Manufacture
Labyrinth Seal Device for Gas Turbine Engine
Moving a Virtual Articulated Object in a Virtual Environment While Avoiding Collisions Between the Articulated Object and the Environment
Moving a Virtual Articulated Object in a Virtual Environment While Avoiding Internal Collisions Between the Articulated Elements of the Articulated Object
Gas Turbine Part Provided with a Protective Coating
Fuel Cell Structure
Turbojet Designed to Be Fixed Onto the Aft Part of the Fuselage of an Aircraft, in Upper Position
Connection Device for Making a Connection Between a Turbomachine Nozzle and a Feed Enclosure for Feeding Cooling Fluid to Injectors
Soundproofing Panel with Beads, and a Method of Manufacture
Variable Cycle Propulsion System with Gas Tapping for a Supersonic Airplane, and a Method of Operation
Protection Mask for Surface Treatment of Turbomachine Blades
Twin-Spool Turbojet with Means for Driving Ancillary Machines
Device for Automatically Mounting and Dismantling Tools on a Robot
Metal Sheet, Including Means for Fixing It to a Support and a Gasket Seal
Throttle Control Device in Particular for Turbine Aero Engine Test Bench
Bearing Support with Double Stiffener
Turbo-Jet Engine with Fan Integral with a Drive Shaft Supported by First and Second Bearings
Monobloc Flameholder Arm for an Afterburner Device of a Bypass Turbojet
Device for Supplying Cooling Air to Exhaust Nozzle Flaps
A Sealing Device with a Brush Gasket and Flexible Washer for a High-Pressure Turbine of a Turbomachine
Turbine Engine with Semi-Fixed Turbine Driving a Receiver Controlled So as to Preserve a Roughly Constant Rotation Speed
Turbofan Jet Engine with Ancillaries Distribution Support
Turbojet Engine Comprising a Connector Arm for Ancillary Systems, and the Connector Arm for Ancillary Systems
Gas Turbine Clearance Control Devices
Cooling Air Evacuation Slots of Turbine Blades
Turbojet Diffuser
Turbofan Engine with the Fan Fixed to a Drive Shaft Supported by a First and a Second Bearing
Method of Measuring the Adhesion of a Coating to a Substrate
Turbojet Architecture with Two Fans at the Front
Turbojet Having a Large Bypass Ratio
Control Lever for the Pitch Angle of a Blade in a Turbomachine
Three-Spool by-Pass Turbojet with a High by-Pass Ratio
Rotor Disk Balancing Device, Disk Fitted with Such a Device and Rotor with Such a Disk
Method of Improving the Ignition Performance of an After-Burner Device for a Bypass Turbojet, and an After-Burner Device of Improved Ignition Performance
Press for Holding and Pressing a Workpiece
Shock Absorber in Elastomer Material for a Suspension Connecting Rod or Other Connecting Component
Turbomachine, for Example a Turbojet for an Airplane
Method of Manufacturing a Hollow Blade for a Turbomachine
Device for Axially Holding a Ring Spacer Sector of a High-Pressure Turbine of a Turbomachine
Process for Manufacturing a Reinforcing Leading or Trailing Edge for a Fan Blade
Turbomachine with a Compact Roller Bearing
Stator of a High-Pressure Turbine of a Turbomachine, and a Method of Assembling It
Device for Tuning Clearance in a Gas Turbine, While Balancing Air Flows
Mounting of Engine Onto an Aircraft Structure
Positioning Bridge Guide and Its Utilisation for the Nozzle Support Pipe of a Turboprop
Device for Balancing a Rotating Part, in Particular a Turbojet Rotor
Device for Axially Retaining Blades on a Turbomachine Rotor Disk
Turboshaft Engine Comprising Two Subassemblies Assembled Under Axial Stress
Turbine Casing Having Refractory Hooks and Obtained by a Powder Metallurgy Method
Aircraft Engine Mount
Forging Die with Marking Means
Device for Assembling Annular Flanges Together, in Particular in a Turbomachine
Ceramic-Based Bushing for a Variable-Pitch Vane System in a Turbomachine
System for Protecting a Main Shaft of an Engine Having a Fusible Bearing
System for Blocking a Main Shaft of an Engine Having a Fusible Bearing
Annular Combustion Chamber for a Turbomachine with an Improved Inner Fastening Flange
Turbine Ring
Hybrid Cycle High Pressure Compressor and Turbine Engine Including Such a Compressor
Fastener System for Fastening Together Parts Using Pins Having Collars
Method for Introducing a Deliberate Mismatch on a Turbomachine Bladed Wheel and Bladed Wheel with a Deliberate Mismatch
Device for Fixing a Burner Ring in an Afterburner Combustion Chamber of a Turbojet Engine
Stationary Ring Assembly for a Gas Turbine
Device for Lubricating a Component in an Assembly of Parts
Device for Fastening a Fluid Duct to a Turbojet Casing
Device for Feeding Air and Fuel to a Burner Ring in an After-Burner Chamber
Aircraft Engine with Means of Suspension from the Structure of an Aircraft
Cooling Device for a Stationary Ring of a Gas Turbine
Checking the Robustness of a Model of a Physical System
Three-Dimensional Machine with Simultaneous Measurements
Lost Wax Moulding Method with Contact Layer
Method of Pickling a Hollow Part in the Form of a Body of Revolution, and Apparatus Implementing Such a Method
Lost Wax Casting Method
Method of Assembling One-Piece Bladed Disks, and a Device for Damping Vibration of the Blades of Such Disks
Tig Welding Method
Gas Turbine Blade Cooling Circuit Having a Cavity with a High Aspect Ratio
Method of Manufacturing or Repairing a Coating on a Metallic Substrate
Installation for Non-Destructive Inspection of a Part
Method and System for Protecting Gas Turbine Fuel Injectors
Installation for Shaping a Hollow Blade
Turbomachine with Means for Axial Retention of the Rotor
Method of Fabricating a Casing for a Turbine Stator
Controlling Air Flow to a Turbine Shroud for Thermal Control
Mounting a Turbine Nozzle on a Combustion Chamber Having Cmc Walls in a Gas Turbine
Gas Turbine Combustion Chamber Made of Cmc and Supported in a Metal Casing by Cmc Linking Members
Mounting a High Pressure Turbine Nozzle in Leaktight Manner to One End of a Combustion Chamber in a Gas Turbine
Assembly Comprising a Gas Turbine Combustion Chamber Integrated with a High Pressure Turbine Nozzle
Aircraft Braking Method and Ducted Fan Jet Engine for Implementing the Method
Stator Turbine Vane with Improved Cooling
Stiffener for Low Pressure Compressor for an Aircraft Engine
Turbojet with Protection Means for a Fuel Injection Device, an Injection Device and a Protective Plate for the Turbojet
Geometrical Construction Process for a Flash Land for the Forging of a Complex Part
Turbo-Jet Engine with a Protective Screen of the Fuel Manihold of a Burner Ring, the Burner Ring and the Protective Screen
Turbomachine Nozzle Cover for Reducing Jet Noise
Assembly Including a Rotary Shaft and a Roller Bearing
Installation Layout for Two Coaxial Shaft Lines
Rotor Disk for a Turbomachine
Nose Cone for a Turbomachine
Convergent Turbojet Exhaust Nozzle
Method and Apparatus for Laser Welding Using a Cw Laser Beam Combined with a Pulsed Laser Beam
Method for Manufacturing Constituents of a Hollow Blade by Rolling
Regulator Feeding Control with Two Flow Rate Laws
Process for the Manufacture by Lost Wax Moulding of Parts That Include at Least One Cavity
Turbomachine with Contrarotating Fans
Gas Turbine or Compressor Blade
Rotor Blade for a Compressor or a Gas Turbine
Method for manufacturing constituents of a hollow blade by press forging
Process for Resurfacing a Monocrystalline or Directionally Solidified Metallic Piece
Retaining of Centring Keys for Rings Under Variable Angle Stator Vanes in a Gas Turbine Engine
Turbofan Jet Engine with an Ancillary-Connecting Arm, and the Ancillary-Connecting Arm
Device for Limiting Turbine Overspeed in a Turbomachine
Control Lever for the Angular Setting of a Stator Blade in a Turboshaft Engine
Turbine Module for a Gas-Turbine Engine with Rotor That Includes a Monoblock Body
Process for Manufacturing the Blade of a Turbomachine, and Assembly of the Cores for Implementation of the Process
Turbine Module for a Gas-Turbine Engine
Effervescent Aerodynamic System for Injecting an Air/Fuel Mixture into a Turbomachine Combustion Chamber
Effervescence Injector for an Aero-Mechanical System for Injecting Air/Fuel Mixture into a Turbomachine Combustion Chamber
Method for Air Circulation in a Turbomachine Compressor, Compressor Arrangement Using This Method, Compression Stage and Compressor Incorporating Such a Arrangement, and Aircraft Engine Equipped with Such a Compressor
Jet Engine with a Variable Section Nozzle of Which at Least One Flap Pivots About a Pin, Pins for Flaps
Welding Tool
Device for Lubricating a Component in a Turbomachine
Device for Supporting and Guiding a Rotating Shaft
Variable-Section Turbomachine Nozzle
Process for the Heating of Forging Machine Tools and Forging Tools, and a Removable Furnace Element for the Heating of Such Tools
Turbine Engine with an Uncoupling Device, Uncoupling Device and Fusible Screw for the Uncoupling Device
Nose-Piece for a Laser-Beam Drilling or Machining Head
Gas Turbine Rotor Blade
Upsetting Method for Working a Metal Slug, Method for Preparing a Slug for a Forging Operation According to the Method and Device for Implementing the Method
Rotary Engine with Shaft Bearing Having Two Stiffnesses, Rotary Engine Shaft and Means of Connection Between a Rotary Engine Shaft and a Bearing
Turbomachine Having a Device for Automatically Detecting Ferromagnetic Particles in an Oil Enclosure
Shroud for a Turbomachine Combustion Chamber
Twin Spool Turbine Engine with Power Take-Off Means on the Low-Pressure and High-Pressure Rotors, and Power Take-Off Module for the Turbine Engine
Part for Protecting the Leading Edge of a Blade
Method of Assembling Two Parts, at Least One of Which Is Made of a Composite, and Insert for Carrying Out the Assembly
A Method of Regulating the Flow Rate of Air in a Rotary Shaft of a Turbomachine
Plain Bearing Between Two Parts Which Are Movable with Respect to Each Other
Turbomachine with a Decoupling Device Common to First and Second Bearings of Its Drive Shaft, Compressor Comprising the Decoupling Device and Decoupling Device
Two-Spool Bypass Turbojet with a Rear Electricity Generator, and an Air Flow Connection Device and System
Turbomachine Including an Integrated Electricity Generator
Fitting of Distributor Sectors in an Axial Compressor
Compensation for an Insufficient Supply of Lubricant in an Inter-Shaft Bearing
Method for Manufacturing Cast Ceramic Cores for Turbomachine Blades
Mechanical Device Comprising a Plurality of Parts Assembled Together with Accurate Relative Positioning
Stator Vane Stage Actuated by a Rotary Actuator Ring Moved by Electric Motor Means
Bipolar Plate for a Fuel Cell
Determining the Extent of a Lateral Shadow Zone in an Ultrasound Inspection Method
Diffuser for an Annular Combustion Chamber, in Particular for an Airplane Turbine Engine
Forging Press of the Hot-Die Type and Thermal Insulation Means for the Press
Member for the Guidance of a Movable Piece
Bearing Assembly Comprising Double Injection of Liquid Lubricant, and Aeronautical Vehicle Comprising at Least One Such Assembly
Powder Mixture Suitable for Sintering to Form a Self-Lubricating Solid Material
Air Bleed Device on a Machine Stator Pivoting Blade
Method for Repairing a Rubbing Surface of a Turbomachine Variable-Pitch Blade
Twin Turbo-Shaft Engine with Accessory Gearbox Drive Means
Method of Using Ultrasound to Inspect a Part in Immersion
Device for the Positioning of a Blade and Bladed Disk Comprising Such a Device
Device for Controlling Variable-Pitch Vanes in a Turbomachine
Taking Air Away from the Tips of the Rotor Wheels of a High Pressure Compressor in a Turbojet
Device for Adjusting the Centering of a Ring for Synchronizing the Control of Pivoting Vanes in a Turbomachine
Device for Varying the Section of the Throat in a Turbine Nozzle
Method for Working a Metal Slug, Sleeve for Implementing the Method
Turbomachine Inner Casing Fitted with a Heat Shield
Method of Repairing a Blisk, and Test Pieces by Welding
Thin Parts Made of Beta or Quasi-Beta Titanium Alloys; Manufacture by Forging
Supporting Collar
Hollow Rotor Blade for the Turbine of a Gas Turbine Engine, the Blade Being Fitted with a "Bathtub"
System for Controlling Stages of Variable-Pitch Stator Vanes in a Turbomachine
System for Controlling Stages of Variable-Pitch Stator Vanes in a Turbomachine
Link Device Between an Enclosure for Passing Cooling Air and a Stator Nozzle in a Turbomachine
Link Device Between an Enclosure for Passing Cooling Air and a Stator Nozzle in a Turbomachine
Deflection System for a Gas Stream in a Nozzle
Suspension for Suspending a Jet Engine on an Aircraft Strut
Exhaust Nozzle for an Engine of a Flying Craft
Assembly Arrangement Between a Bearing Inner Race and a Journal, Race and Journal Suitable for Such an Arrangement, and Turbomachine Fitted Therewith
Balancing Device of a Turbomachine Engine
Stator Blades, Turbomachines Comprising Such Blades and Method of Repairing Such Blades
Swivelling Exhaust Nozzle for an Aircraft Engine
Sealing Device for a Chamber of a Turbomachine, and Aircraft Engine Equipped with Said Sealing Device
Device for Feeding Fuel to a Combustion Chamber in a Turbomachine
Easily Demountable Combustion Chamber with Improved Aerodynamic Performance
Turbine Module for a Gas Turbine Engine
Method of Calibrating the Mass of Components Intended to Be Mounted at the Periphery of a Rotor
Antirotation Injection System for Turbojet
Process for Manufacturing a Tubular Component with an Insert Made of a Metal Matrix Composite
Process for Manufacturing a Coiled Insert of Coated Filaments
Process for Manufacturing a Bonded Sheet Composed of Ceramic Filaments with a Metal Matrix, Device for Implementing Said Process, Bonded Sheet Obtained by Said Process
System of Attaching an Injection System to a Turbojet Combustion Chamber Base
Mechanical Part and Method of Manufacturing Such a Part
Device for Rotationally Locking a Clamping Nut for a Component on a Shaft, Clamping Nut and Shaft Comprising It, and Aircraft Engine Equipped Therewith
Method of Inspecting the Profile of the Connection Zone Between the Cylindrical Portion and the Taper of a Roller for a Turbomachine Roller Bearing
Closure and Locking Detection System for Turbojet Thrust Reverser
Turbomachine Rotor Including at Least One Disk Reinforced by a Composite Ring
Device for Supporting and Housing Auxiliaries in a Bypass Turbojet
Thrust Orienting Nozzle
Process for Manufacturing a Component with an Insert Made of a Composite Consisting of a Metal Matrix and Ceramic Fibers
Assembling an Annular Combustion Chamber of a Turbomachine
Cooling Circuits for a Turbomachine Moving Blade
A Device for Damping Vibration of a Ring for Axially Retaining Turbomachine Fan Blades
Method of Repairing a Blade of a One-Piece Bladed Disc of a Turbomachine and Test Piece for Implementing the Method
Core for Turbomachine Blades
Checking of Turbomachine Blades
Compressor with Centripetal Air Takeoff
Sealing System for the Rear Lubricating Chamber of a Jet Engine
Metal Component Treated by Putting Sublayers in Compression, and Method of Obtaining Such a Component
Compressor Comprising a Plurality of Cells Reconstituting an Annular Volume of Separation of Flows in a Turbine Engine
Method of Assembling a Turbomachine
Air Deflector for a Cooling Circuit for a Gas Turbine Blade
Device for Blocking a Ring for Axially Retaining a Blade, Associated Rotor Disk and Retaining Ring, and Rotor and Aircraft Engine Comprising Them
Device for Blocking a Ring for Axially Retaining a Blade, Associated Rotor Disk and Retaining Ring, and Rotor and Aircraft Engine Comprising Them
Device for Heating a Cylindrical Component and Use in Assembling an Inter-Shaft Bearing in a Turbomachine
Combustion Chamber for a Turbomachine
Combustion Chamber of a Gas Turbine Engine with an Upstream Fairing for Separating the Gas Stream, Annular Wall Forming a Cap of the Upstream Fairing of the Chamber, and Gas Turbine Engine with the Chamber
Hollow Turbomachine Blade
Multistage Turbomachine Compressor
Turbomachine with Angular Air Delivery
Turbomachine Blade, in Particular a Fan Blade, and Its Method of Manufacture
Turbomachine Blade
Cooling Channel Formed in a Wall
Bushing for a Variable-Pitch Vane Pivot in a Turbomachine
Locking of the Blades in a Fan Rotor
Assembly of a Labyrinthe Seal Support on a Turbine Machine Rotor
Link Device of Controllable Variable Length
Shim for a Turbojet Blade
Pivot Bushing for a Variable-Pitch Vane of a Turbomachine
Structural Turbine Engine Casing
Nozzle Ring with Adhesive Bonded Blading for Aircraft Engine Compressor
Device for Controlling Clearance in a Gas Turbine
Device for Guiding an Element in an Orifice in a Wall of a Turbomachine Combustion Chamber
Method for Metallic Coating of Fibres by Liquid Technique
Performance of a Combustion Chamber by Multiple Wall Perforations
Method and Device for Synchrophasing the Propellers of an Aircraft with Several Propulsion Units
A Method of Forming a Thermal Protective Coating on a Super Alloy Metal Substrate
Variable-Setting Stator Blade Guidance Device in an Axial Turbomachine
Fastening a Combustion Chamber Inside Its Casing
Method of Manufacturing a Composite Turbomachine Blade, and a Blade Obtained by the Method
Method and System for Detecting and Measuring the Disturbances in Terms of Frequency of the Rate of Rotation of a Rotor
Device for Ventilating Turbine Disks in a Gas Turbine Engine
Cooling Layout for a Turbine Blade, Turbine Blade Included Therein, Turbine and Aircraft Engine Equipped Therewith
Method of Making a Wiper for a Sealing Labyrinth, and a Thermomechanical Part and a Turbomachine Including Such a Wiper
Annular Wiper for a Sealing Labyrinth, and Its Method of Manufacture
Thermostructural Turbomachine Part That Is Circularly Symmetrical About a Longitudinal Axis, the Part Including an Annular Wiper, and a Method of Manufacture
Combustion Chamber End Wall with Ventilation
Method of Making a Rim Situated at the Free End of a Blade, a Blade Obtained by the Method, and a Turbomachine Fitted with the Blade
Central Cooling Circuit for a Moving Blade of a Turbomachine
Device for Injecting a Mixture of Air and Fuel, and a Combustion Chamber and Turbomachine Provided with Such a Device
Device for Attaching a Flame-Arrestor Arm to an Afterburner Casing and Afterburner Comprising Such a Device
Turbine Blade with Cooling and with Improved Service Life
Bladed Stator for a Turbo-Engine
Impeller and Diffuser with a Rotating and Converging Hub
Pump Comprising an Axial Balancing System
Tension Decoupler Device
Cooling of a Multimode Fuel Injector for Combustion Chambers, in Particular of a Jet Engine
Core Exhaust Mixer, Having a Variable Area, for Turbo-Fan Jet Engines of Supersonic Aircraft
Multimode Fuel Injector for Combustion Chambers, in Particular of a Jet Engine
Balancing Flyweight, Rotor Disk Equipped Therewith, Rotor and Aircraft Engine Comprising Them
Radially-Compact Assembly Between a Turbine Shaft and a Stub Axle of a Turbomachine Compressor Shaft
Hollow Rotor Blade for the Turbine of a Gas Turbine Engine
Assembly of Sectorized Fixed Stators for a Turbomachine Compressor
Turbomachine with Integral Generator/ Starter
Attachment Unit of Driving Shaft with Tensioner Nut
Air Inlet for a Turbofan Engine
Turbofan Exhaust System
Method of Fabricating a Combustion Chamber
Method of Manufacturing a Turbomachine Component That Includes Cooling Air Discharge Orifices
System for Connecting an Engine Shaft with a Retractable Nut
Turbomachine Rotor Wheel
Turbine Engine Combustion Chamber with Tangential Slots
Combustion Chamber in a Turbomachine
Device for Adjusting the Centring of a Turbo-Engine Pivoting Vane Control Synchronization Ring
Transverse Wall of a Combustion Chamber Provided with Multi-Perforation Holes
Turbine Engine Annular Combustion Chamber with Alternate Fixings
Annular Combustion Chamber of a Turbomachine
Laser Cutting Method
Annular Combustion Chamber of a Turbomachine
Method of Depositing a Thermal Barrier by Plasma Torch
Annular Combustion Chamber with a Removable End Wall
Rotary Cutting Tool Comprising Two Cutting Portions Having Opposed Cutting Directions
Arrangement for a Jet Engine Combustion Chamber
System for Measuring Dimensions Inside a Hollow Shaft, Particularly One Belonging to an Aeronautical Turbomachine
Casing Cover in a Jet Engine
Process for Manufacturing the Blade of a Turbomachine, and Assembly of the Cores for Implementation of the Process
System for Deicing an Aircraft Turbine Engine Inlet Cone
Central Body of a Turbojet Nozzle
Method for the Monobloc Sizing for the Tempering Casings and Device for Implementing the Method
Device for Attaching Ring Sectors Around a Turbine Rotor of a Turbomachine
Configuration of Dilution Openings in a Turbomachine Combustion Chamber Wall
Device for Injecting a Mixture of Air and Fuel, Combustion Chamber and Turbomachine Both Equipped with Such a Device
Assembly Comprised of a Vane and of a Cooling Liner, Turbomachine Nozzle Guide Vanes Assembly Comprising This Assembly, Turbomachine and Method of Fitting and of Repairing This Assembly
Stator Vane with Localized Reworking of Shape, Stator Section, Compression Stage, Compressor and Turbomachine Comprising Such a Vane
Flameholder Arm for an Afterburner
Device for Attaching Ring Sectors to a Turbine Casing of a Turbomachine
Device for Cooling a Turbomachine Turbine Casing
Device for Mounting an Air-Flow Dividing Wall in a Turbojet Engine Afterburner
Retaining Device for Axially Retaining a Rotor Disk Flange in a Turbomachine
Turbomachine Variable-Pitch Stator Blade
Optimized Aerodynamic Profile for a Turbine Blade
System for Retaining Blades in a Rotor
Measurement of Wall Thicknesses Particularly of a Blade,by Eddy Currents
Exhaust Assembly Forming a Horizontal Propulsion Gas Elbow in an Aircraft
Elbow-Shaped Propulsion Gas Exhaust Assembly in an Aircraft
Exhaust Assembly Forming a Horizontal Propulsion Gas Elbow in an Aircraft
Turbojet Engine Comprising an Afterburner Duct Cooled by a Variable-Throughput Ventilation Stream
Central Body for a Turbojet Exhaust Channel, Turbojet
Assembly for an Aircraft Engine Compressor Comprising Blades with Hammer Attachment with Inclined Root
Process for Manufacturing Ceramic Cores for Turbomachine Blades
Combustion Chamber of a Turbomachine
Shielded and Sealed Electric Harness
Method of Fabricating a Turbomachine Rotor Disk
Device for Guiding a Stream of Air Entering a Combustion Chamber of a Turbomachine
Bleed System for a Low-Pressure Compressor of a Turbomachine
Turbomachine Nozzle Cover Provided with Triangular Patterns Having a Point of Inflexion for Reducing Jet Noise
Turbomachine Nozzle Cover Provided with Triangular Patterns Having Pairs of Vertices for Reducing Jet Noise
Turbomachine Stator Including a Stage of Stator Vanes Actuated by an Automatically Centered Rotary Ring
Sector of a Compressor Guide Vanes Assembly or a Sector of a Turbomachine Nozzle Assembly
Part-Holding Device in a Repairing Method for a Blade of a Monobloc Bladed Disc in a Turbo-Machine
Rotary Motion Mixer for a Converging-Stream Nozzle of a Turbomachine
Exhaust Cone for Channeling a Stream of Gas Downstream from a Turbine
Bearing for Variable Pitch Stator Vane
Device for Injecting a Mixture of Air and Fuel, and Combustion Chamber and Turbomachine Provided with Such a Device
Device for Injecting a Mixture of Air and Fuel, and Combustion Chamber and Turbomachine Provided with Such a Device
Device for Injecting a Mixture of Air and Fuel, and Combustion Chamber and Turbomachine Both Equipped with Such a Device
Turbomachine Combustion Chamber Arrangement Having a Collar Deflector
Arrangement with a Twist-Lock Coupling for a Turbomachine Combustion Chamber
Turbomachine Rotor and Turbomachine Comprising Such a Rotor
Turbine Engine with an Alternator and Method for Transmitting Movement to an Alternator
Method for Treating Oil Waste in a Gas Turbine Engine
Process for Manufacturing a Blisk and Mold for Implementing the Process
Gas Exhaust Nozzle for a Bypass Turbomachine Having an Exhaust or Throat Section That Can Be Varied by Moving the Secondary Cowl
Ventilation of a Downstream Cavity of an Impeller of a Centrifugal Compressor
Diffuser/Guide Vane Assembly for a Turbomachine
System for Cooling a Downstream Cavity of a Centrifugal Compressor Impeller
System for Ventilating a Downstream Cavity of an Impellor of a Centrifugal Compressor
Bypass Turbomachine with Artificial Variation of Its Throat Section
System for Ventilating a Combustion Chamber Wall in a Turbomachine
Turbomachine Comprising a System for Cooling the Downstream Face of an Impeller of a Centrifugal Compressor
System for Ventilating a Combustion Chamber Wall
Cylindrical-Rod Device for Controlling a Variable-Pitch Vane of a Turbomachine
Electric Supply for an Aircraft Gas Turbine Engine Equipment
Device for Supplying Fuel to a Gas Turbine Engine with Regulated Fuel Flow Rate
Aircraft Engine Fuel Supply
Method for Detecting and Quantifying Drilling Anomalies
Method for Evaluating the Fatigue Strength of Welded Joints
Process for Manufacturing Single-Crystal Seeds Simultaneously with the Casting of Single-Crystal Parts
Turbomachine Rotor Blade
Annular Combustion Chamber for a Turbomachine
Device for Driving the Rotor of Turbine Engine Auxiliary
Turbomachine Fan Duct
Composite Turbomachine Blade with Metal Reinforcement
Integrated Propulsive System Comprising a Bypass Turbojet Engine
Propulsion System with Integrated Pylon
Annular Turbomachine Combustion Chamber
Set of Insulating Sheets on a Casing to Improve Blade Tip Clearance
Device for Attaching a Stator Vane to a Turbomachine Annular Casing, Turbojet Engine Incorporating the Device and Method for Mounting the Vane
Sealing System Between Two Coaxial Rotary Shafts
Fuel Injector for a Gas Turbine Engine Combustion Chamber
Transition Channel Between Two Turbine Stages
Fan Platform Fin
Turbojet Engine Accessory Gear Box Driveshaft; Modular Additional Accessory
Moving Blade for a Turbomachine
Swiveling Device for a Bell Crank Fork
Method and Device for Reducing the Speed in the Event of Breakage of a Gas Turbine Engine Turbine Shaft
Balancing System for Turbomachine Rotor
Method of Fabricating a Test Blade of Composite Material
Method of Fabricating a Test Blade of Composite Material
Device for Limiting Turbine Overspeed in a Turbomachine
Balancing System for Turbomachine Rotor
Bearing Arrangement for a Rotating Shaft, and Turbine Engine Equipped with Such an Arrangement
Hardened Martensitic Steel, Method for Producing a Component from This Steel and Component Obtained in This Manner
Turbomachine Turbine Ring Sector
Swept Turbomachine Blade
Coupling Device for a Turbine Upstream Guide Vane, a Turbine Comprising Same, and Aircraft Engine Fitted Therewith
Turboprop Including a Set of Adjustable-Pitch Blades
Fastener Device for Fastening a Free Turbine Stator with Dual Centering
Device for Connecting Two Rotating Shafts, in Particular in a Turbomachine
Method for Laser Drilling a Component Made of a Ceramic Matrix Composite, the Method Including a Step of Trepanning and a Step of Removing Slag by Enlarging the Laser Beam, Hole Obtained by This Method, Component Made of a Ceramic Matrix Composite Containing It, and Turbojet Comprising Such a Component.
Chamber Endwall, Method of Producing It, Combustion Chamber Comprising It, and Turbine Engine Equipped Therewith
Deflector for a Combustion Chamber Endwall, Combustion Chamber Equipped Therewith and Turbine Engine Comprising Them
Target for Vaporizing Under an Electron Beam, a Method of Fabricating It, a Thermal Barrier and a Coating Obtained from a Target, and a Mechanical Part Including Such a Coating
Target for Vaporizing Under an Electron Beam, a Method of Fabricating It, a Thermal Barrier and a Coating Obtained from a Target, and a Mechanical Part Including Such a Coating
Electric Connector Assembly Having a Device for Protection Against Pollution
Pump with an Elastic Device on a Rolling Bearing
Robotic Machining Tool Employing an Endless Machining Belt
Turbomachine Combustion Chamber
Two-Stage Fuel Injector
Rotor Disk for Turbomachine Fan
Fuel-Injection Device in a Turbomachine
Device for Storing and Dispensing Endless Machining Belts for a Robotic Installation
Joining Device for Joining Two Assemblies, for Example for a Stator of a Turbomachine
Turboprop Having a Propeller Made Up of Variable-Pitch Blades
Dual-Injector Fuel Injector System
Tubular Part That Includes an Insert Made of a Metal Matrix Composite
Gas Turbine Engine Diffuser and Combustion Chamber and Gas Turbine Engine Comprising Same
Method for the Modular Balancing of a Turbomachine Rotor
Turboprop with a Variable-Pitch Propeller
Acoustic Flow Straightener for Turbojet Engine Fan Casing
Variable-Section Flow Mixer for a Double-Flow Turbojet for a Supersonic Airplane
Device for Measuring the Position of a Piston in a Cylinder
Relief Device for a Turbojet and a Turbojet Comprising Same
System for Deicing the Nose Cone of an Aircraft Turbojet with Oil
Method of Taking Off Auxiliary Power from an Airplane Turbojet, and a Turbojet Fitted to Implement Such a Method
Air Intake Circuit Arrangement for High Pressure Compressor of a Turbine Engine
Device and Method of Standby Lubrication for an Engine
Method of Building Up an Aluminum Alloy Part
Method of Manufacturing a Gas Turbine Casing Out of Composite Material, and a Casing as Obtained Thereby
Turbomachine Casing with Treatment, a Compressor, and a Turbomachine Including Such a Casing
Optimized Aerodynamic Airfoil for a Turbine Blade
Control of Variable-Pitch Blades
Alignment Control for a Water-Jet Cutting System
Method for Reducing Vibration Levels of a Bladed Wheel in a Turbomachine
Aeroengine Fitted with Heat Exchanger Means
De-Oiler System for an Aircraft Engine.
Turbine Stage in a Turbomachine
High-Pressure Turbine of a Turbomachine
Turbomachine Fan
Method of Detecting Damage to an Engine Bearing
Rotary Cutting Tool Comprising Two Cutting Portions Having Opposed Cutting Directions
Turbomachine Exhaust Case Drain
Turbomachine Fan
Turbomachine Rotor Disk
Turbomachine with a Deflector System
Airtight External Shroud for a Turbomachine Turbine Wheel
Inter-Turbine Casing with Cooling Circuit, and Turbofan Comprising It
Rotary Assembly for a Turbomachine Fan
Actuator Position Control Device Using a Fail Freeze Servo-Valve
Fairing for a Combustion Chamber End Wall
Fan Blade
Elbow Connection for Multiple-Wire Electric Cable
Brazed Joint Between a Titanium-Based Metal Part and a Ceramic Part Based on Silicon Carbide (Sic) and/or Carbon
Joint Between a Metal Part and a Ceramic Part Based Sic and/or C
Brazed Joint Between a Metal Part and a Ceramic Part
Tool for Manufacturing Ceramic Casting Cores for Turbomachine Blades
By-Pass Turbojet Including a Thrust Reverser
Device for Inspecting a Rectilinear Cavity with Eddy Currents
Flexible Suspension for Turbine Engine
Method and an Installation for Using Eddy Currents for Non-Destructive Inspection with Automatic Calibration
Method of Making a Deposit on an Sic-Covered Substrate
Method of Making a Device for Measuring Deformation
Damper for Turbomachine Vanes
Device for Producing Electrical Power in a Two-Spool Gas Turbine Engine
Gate Valve for a System for Circulating Cooling Air Through a Turbomachine
Device for Non-Destructive Eddy Current Inspection of a Hole Formed in a Conductive Part
Process and Device for Coating Fibers with a Metal by a Liquid Method
System for Dissipating Energy in the Event of a Turbine Shaft Breaking in a Gas Turbine Engine
System Providing Braking in a Gas Turbine Engine in the Event of the Turbine Shaft Breaking
Ultrasound Prediction of Workpiece Deformation
Identification of Points of Interest in a Region of the Surface of a Part and Application to the Optimization of the Path and of the Angular Position of Eddy Current Probes
Air Reinjection Compressor
Turbomachine Combustion Chamber with Helical Air Flow
Exhaust Casing for a Turbomachine
Exhaust Casing Hub Comprising Stress-Distributing Ribs
Long-stroke regulator valve with a stop function
Device for Cooling the Slots of a Rotor Disk in a Turbomachine Having Two Air Feeds
Damping Device for Turbomachine Stator
Spacer Interposed Between a Blade Root and the Bottom of a Slot in the Disk in Which the Blade Is Mounted
Movable Impeller for a Turbojet and Turbojet Comprising Same
Installing a Shaft in a Bearing Comprising a Self-Releasing Nut
Damping Device for a Shaft of a Turbomachine
Device for Cooling Slots of a Turbomachine Rotor Disk
Suspension for Suspending a Turbine Engine from the Structure of an Aircraft
Device for Axially Retaining Blades Mounted on a Turbomachine Rotor Disk
Tool for Rammer Die-Cutting
Dynamic Brush Seal
Twin Fan Turbomachine
Optimizing an Anti-Coke Film in an Injector System for a Gas Turbine Engine
Device for Supplying Ventilation Air to the Low Pressure Blades of a Gas Turbine Engine
Combustion Chamber Comprising Chamber End Wall Heat Shielding Deflectors and Gas Turbine Engine Equipped Therewith
System and a Method for Regulating the Temperature of a Fuel Cell
Turbomachine with a Diffuser
Device for Attaching a Combustion Chamber
External Fan Duct Casing in a Turbomachine
Turbojet Comprising a Current Generator Mounted in the Fan and a Method of Mounting Said Generator in the Fan
Ceramic Drill Bit for High-Speed Drilling of Composites
Assistance and Emergency Backup for the Electrical Drive of a Fuel Pump in a Turbine Engine
Fuel Injector for Injecting Fuel into a Turbomachine Combustion Chamber
Turbine Nozzle Sector
Multipoint Injector for Turbomachine
Slotting Milling Cutter for Machining with a High Feed and a Low Pass Depth
Bypass Turbomachine with Reduction of Jet Noise
Apparatus for Searching for and Detecting Defects in Parts by Endoscopy
Turbomachine Diffuser
Aircraft Turbomachine Fan Comprising a Balancing Flange Concealed by the Inlet Cone
Variable-Pitch Vane of a Turbomachine
Gas Turbine Engine with a Means of Driving the Accessory Gear Box, and Method of Fitting Said Engine
Stage of Variable-Pitch Vanes for a Turbomachine
Turbomachine with Annular Combustion Chamber
Turbomachine Combustion Chamber with Helical Air Flow
Separator for Feeding Cooling Air to a Turbine
Pylon for Suspending an Engine Beneath an Aircraft Wing
Electricity Generation in a Turbomachine
Component Ventilation and Pressurization in a Turbomachine
Actuating Device, Bypass Air Bleed System Equipped Therewith, and Turbojet Engine Comprising These
Use of an Activiating Flux for the Tig Welding of Metal Parts
Device for Validating Measurements of a Dynamic Magnitude
Member for Locking Ring Sectors Onto a Turbomachine Casing, Comprising Means Allowing It to Be Grasped
Lever for Rotating a Turbomachine Variable-Pitch Stator Vane About Its Pivot
Damping Device for Composite Blade
Sealing a Rotor Ring in a Turbine Stage
Method of Recuperating Turbine Elements
Annular Combustion Chamber for a Gas Turbine Engine
Steerable Structure of Catheter or Endoscope Type
A Method of Using Laser Shock Impacts to Produce Raised Elements on a Wall Surface Capable of Being Swept by a Fluid in Order to Control the Intensity of Turbulence in a Transition Zone
Shim for a Turbomachine Blade
Combustion Chamber of a Turbomachine Including Cooling Grooves.
Circular-Shaping Device for a Rotating Part, Especially an Exhaust Housing of a Turbo Engine
Method of Aluminization in the Vapor Phase on Hollow Metal Parts of a Turbomachine
Process for the Vapor Phase Aluminization of a Turbomachine Metal Part and Donor Liner and Turbomachine Vane Comprising Such a Liner
Method of Retouching Metal Parts
Intermediate Casing of a Turbojet and a Turbojet
Fuel Feed Circuit for an Aircraft Engine
Turbojet Having an Electricity Generator Arranged in Its Fan
Turbine Stator for Aircraft Turbine Engine Including a Vibration Damping Device
Pitch Control Ring for Stator Vanes of a Turbomachine
Turbine Engine Wheel
Connecting Radial Arms to a Circular Ferrule by Imbricating Attached Parts
Cooled Blade for a Turbomachine
Control of Clearance at Blade Tips in a High-Pressure Turbine of a Turbine Engine
Iso-Kinetic Probe for the Analysis of the Pollution of Gases Generated by an Aircraft Engine
Stage of a Turbine or Compressor, Particularly for a Turbomachine
Connection of Radial Arms to a Circular Sleeve via Axes and Spacers
Annular Combustion Chamber of a Gas Turbine Engine
Means for Preventing the Rotation of a Pin Supporting a Turbine Engine Suspension Member
Method for Attaching a Bearing Supporting a Rotor on a Turbomachine
Turbine or Compressor Stage for a Turbojet
Turbine or Compressor Stage for a Turbomachine
Relief Valve in a Turbomachine
Assembly of a Fan Blade and of Its Damper, Fan Blade Damper and Method for Calibrating the Damper
Metal Impeller Blade Manufactured by Molding and Method of Manufacturing the Impeller Blade
Device for Detecting Breakage of a Turbomachine Shaft
Fan Nozzle of Adjustable Section
Turbojet Suspended from an Aircraft Mast
Preheating Heat Exchanger for a Fuel Cell
Turbomachine Blade
Device for Guiding an Element in an Orifice in a Wall of a Turbomachine Combustion Chamber
Suspension for Mounting a Turbojet Engine on an Aircraft
Method of Designing a Multistage Turbine for a Turbomachine
Panel for Supporting Abradable Material in a Turbomachine
Sectorized Nozzle for a Turbomachine
Mounting Tubes for Pressurizing an Internal Enclosure in a Turbomachine
Sealing a Hub Cavity of an Exhaust Casing in a Turbomachine
Device for Bleeding Air from a Turbomachine Compressor
Composite coupling with a machining portion
Turbomachine Module Provided with a Device to Improve Radial Clearances
System for Injecting a Mixture of Air and Fuel into a Turbomachine Combustion Chamber
Turbomachine Combustion Chamber
Turbomachine Blade That Is Cast with a Local Fattening of the Section of the Airfoil
Intermediate Casing Extension for an Aircraft Jet Engine, Comprising a Sectorised Annular Groove for Receiving the Nacelle Covers
Intermediate Casing for an Aircraft Jet Engine, of Improved Design
Method and a System for Characterizing and Counting Violations of a Threshold by an Aircraft Engine Operating Parameter
Method of Selecting an Arrangement of Sectors for a Turbomachine Nozzle
Connecting a Propulsion System to a Structural Element of an Aircraft
Gas Turbine Engine with Valve for Establishing Communication Between Two Enclosures
Twin-Airfoil Blade with Spacer Strips
Arrangement of a Semiconductor-Type Igniter Plug in a Gas Turbine Engine Combustion Chamber
Centering a Part Inside a Shaft
Surfacing and Contouring Cutter for High-Speed Machining of Composite Material Parts
Turbomachine Shaft Guidance
Turbojet Compressor
Attachment of a Multiflow Turbojet Engine to an Aircraft
Deoiling Device and Turbomachine Comprising This Device
Diffuser-Nozzle Assembly for a Turbomachine
Split Ring for a Rotary Part of a Turbomachine
Oil Recovery Device
Detecting the Clogging of a Fluid Filter
Process for Manufacturing Directionally Solidified Blades
Blade with a Cooling Groove for a Bladed Wheel of a Turbomachine
Device for Mounting an Igniter Plug in a Combustion Chamber of a Gas Turbine Engine
Branch Connection Stub, a Branch Connection Device Comprising a Main Pipe and Said Branch Connection Stub, and a Method of Connecting Such a Branch Connection Stub by Welding
Device for Controlling a Regulated System, and an Engine Including Such a Device
Flame Holder for an Afterburner Duct of a Jet Engine with a Spacer Shoe, Afterburner Duct, and Jet Engine Comprising an Afterburner Duct
Control Device of Variable Pitch Vanes in a Turbomachine
Optimizing the Angular Positioning of a Turbine Nozzle at the Outlet from a Turbomachine Combustion Chamber
Fan Rotor for a Turbomachine or a Test Engine
Turbomachine Casing Including a Device for Preventing Instability During Contact Between the Casing and the Rotor
Thermomechanical Part Constituting a Body of Revolution About a Longitudinal Axis and Including at Least One Abradable Ring for a Sealing Labyrinth
Asymmetrical Member for Locking Ring Sectors to a Turbine Engine Casing
Device for Inspecting Tangential Recesses in a Rotor Disk
Solid Oxide Fuel Cell Comprising a Thermal Exchanger Placed Concentrically Relative to a Cell Core
System for Controlling a Plurality of Turbomachine Discharge Valves
Device for the Axial Locking of a Guide Shaft Bearing in a Turbomachine
Bypass Turbojet
Bearing Support Journal and Assembly of Such a Journal and a Sealing Sleeve
Turbo-Engine Compressor Tip Comprising De-Icing Means
Turbomachine with a Long Lasting Position-Holding System
Cryogenic Liquid Storage System for a Spacecraft
Actuating of a Thrust Reverser in a Turbomachine
Cooling Air Bleed Device in a Turbine Engine
Cooling Air Bleed Device in a Turbomachine
Regulating the Flow Rate of Fuel Taken from a Fuel Circuit of an Aircraft Propelled by an Engine
Emitter for Ionic Thruster
Method of Repairing Machined Components Such as Turbomachine Blades or Blades of Blisks
Optimized Aerodynamic Profile for a Turbine Blade
Turbomachine Combustion Chamber
Turbomachine with Integral Generator/Starter
Method for Reducing the Vibration Levels of a Propeller of a Turbine Engine
Method for Reducing the Vibration Levels of a Propfan of Contrarotating Bladed Disks of a Turbine Engine
System for Controlling at Least Two Variable-Geometry Equipments of a Gas Turbine Engine, Particularly by Rack
System for Controlling at Least Two Variable-Geometry Equipments of a Gas Turbine Engine, Particularly by Cam Mechanism
System for Controlling Variable-Geometry Equipments of a Turbomachine, Particularly by Articulated Bellcranks
Method for Fitting and Protecting a Sensor on a Substrate
Method for the Monobloc Sizing for the Tempering Casings and Device for Implementing the Method
Aircraft with Reciprocating Engines Partially Embedded in the Fuselage
Device for Tapping Cooling Air in a Turbomachine
Device for Regulating the Flow Rate of Air Feeding a Turbine Ventilation Cavity of a Turbomachine Turbine Section
Turbomachine Having an Unducted Fan Provided with Air Guide Means
Stator Vane Stage Actuated by an Automatically-Centering Rotary Actuator Ring
Patent:
42,523 →
Application:
12/620,630 →
Turbomachine with Separate Fuel Injection Systems, Using Identical Sealing Joints
Turbomachine Rotor Having Blades of Composite Material Provided with Metal Labyrinth Teeth
Platform Seal in a Turbomachine Rotor, Method for Improving the Seal Between a Platform and a Turbomachine Blade
Turbomachine Rotor Wheel Having Composite Material Blades
Turbine Engine with a Power Turbine Equipped with an Electric Power Generator Centered on the Axis of the Turbine Engine
Turbine Engine with a Power Turbine Equipped with an Electric Power Generator
Mechanical Component Comprising an Insert Made of Composite
Mechanical Component Comprising an Insert Made of Composite
Fuel Injection Systems in a Turbomachine Combustion Chamber
Closed Electron Drift Thruster
Afterburner Chamber for a Turbomachine
Turbine Shroud Ring with Rotation Proofing Recess
Bypass Engine with Contrarotating Turbine Wheels Including a Reversing Module
Blade Made of Composite Material Comprising a Damping Device
Controllable Pitch Blade Non-Ducted Propeller for Jet Engine
Method of Monitoring a Thrust Reverser
Monitoring of a High-Pressure Pump in a Turbine Engine Fuel Supply Circuit
Former for Fabricating a Composite Material Casing for a Gas Turbine
Cooling Channel Formed in a Wall
Method of Depositing a Thermal Barrier by Plasma Torch
Device for the Non-Destructive Testing of Parts in a Turbomachine
Method of Developing and Calibrating a Tool for Non-Destructive Inspection of Parts of a Turbomachine
Impeller Which Includes Improved Means of Cooling
Anti-Wear Device of a Turbomachine Rotor
Method to Manufacture a Hollow, Single-Piece Bladed Disc
Collar for Maintaining Electric Cables
Method and System for Detecting the Ingestion of an Object by an Aircraft Turbine Engine During a Mission
System for Controlling a Plurality of Functions of a Turbojet Engine
Hardened Martensitic Steel, Method for Producing a Component from This Steel and Component Obtained in This Manner
Hardened Martensitic Steel, Method for Producing a Component from This Steel and Component Obtained in This Manner
Monitoring a Filter Used for Filtering a Fluid in an Aircraft Engine
Balancing Device and Method
Hall Effect Thruster with Cooling of the Internal Ceramic
Ventilation for a Turbine Wheel in a Turbine Engine
Device Adapted to Be Fitted with Propeller Blades
Mechanical Drive Device for Driving the High Pressure Sub Assembly of an Airplane Engine
Turbomachine Combustion Chamber
Device for Testing the Coating of a Vane Base
Method for Testing the Coating of a Vane Base
Blade with Non-Axisymmetric Platform: Recess and Boss on the Extrados
Diffuser for Turbine Engine Including Indented Annular Webs
Blade with Non-Axisymmetric Platform
Heat Exchanger System
Cooling of the Tip of a Blade
Method for Manufacture of an Integrally Bladed Rotor, with Temporary Blade-Holding Ring
Nozzle for a Turbomachine Turbine
System of Counter-Rotating Propellers with a Feathering Device for Propeller Blades
Method for Forming a Protective Coating Containing Aluminium and Zirconium on a Metal Part
Process for Manufacturing a Single-Piece Blisk with a Temporary Blade Support Ring Arranged at a Distance from Blade Tips
Process for Manufacturing a Single-Piece Blisk by Cutting with an Abrasive Water Jet
Process for Manufacturing a Single-Piece Blisk with a Temporary Blade Support Ring Removed Before a Milling Finishing Step
Process for Manufacturing a Single-Piece Blisk with a Temporary Blade Support Ring Removed After a Milling Finishing Step
Improved Process for Manufacturing a Single-Piece Blisk with a Temporary Blade Support Ring Removed Before a Milling Step
Method and a Device for Balancing Pressure in a Turbojet Bearing Enclosure
Casing for a Moving-Blade Wheel of Turbomachine
Turbomachine Rotor Comprising an Anti-Wear Plug, and Anti-Wear Plug
Device for Controlling Variable-Pitch Blades in a Turbomachine Compressor
Device for Axial Retention of Mobile Vanes Mounted on a Rotor Disc
Guide for an Ignition Plug in a Turbomachine Combustion Chamber
Fuel Supply Installation of an Aircraft Turbojet
Turbojet Nacelle
Process and Device for Coating Fibers with a Metal by a Liquid Method
Nozzle Stage for a Turbomachine Compressor
Turbomachine Compressor Rotor Including Centripetal Air Bleed Means
Wall Cooling Device
Method for Ultrasound Shot-Blasting of Turbomachine Parts
Method for Deburring a Ceramic Foundry Core
Turbine Nozzle for a Turbomachine
Centripetal Air Bleed from a Turbomachine Compressor Rotor
Unit for Locking Ring Sectors on a Turbomachine Casing, Comprising Radial Passages for Gripping It
Injection of Air into the Flow Path of a Turbomachine Compressor
Air Conditioner
Roller Conveyor Motorized Roller and Roller Conveyor Device Using the Same
Annular Combustion Chamber for a Gas Turbine Engine
Simplified System for Controlling Propeller Blade Pitch in an Aircraft Turboshaft Engine
Simplified System for Controlling Propeller Blade Pitch in an Aircraft Turboshaft Engine
Turbine Engine with Diffuser
Gas Turbine High Pressure Compressor Fluid Return and Reinjection Including an Annular Air Bleeding Manifold
Assembly Including a Turbine Disk for a Gas Turbine Engine and a Bearing-Supporting Journal, and Cooling Circuit for the Turbine Disk of Such an Assembly
Manufacture of a Portion of a Metal Part Using the Mig Method with Pulsed Current and Wire
High Pressure Turbine of a Turbomachine with Improved Assembly of the Mobile Blade Radial Clearance Control Box
Annular Flange for Fastening a Rotor or Stator Element
Turbomachine Fan Rotor
Turbomachine Compressor with an Air Injection System
Structural Frame for a Turbomachine
Gas Turbine Engine Combustion Chamber Comprising Cmc Deflectors
Fairing Device for Nacelle of an Aircraft Propulsion Power Unit
Air Discharge System for an Aeronautical Turbine Engine Compressor
Method and System for Determining the Angular Position of a Turbojet Engine Rotor
Turbomachine Compressor
Axial-Centrifugal Compressor Having System for Controlling Play
Aircraft Propulsion System
Device for Fastening a Variable Pitch Blade
Method of Manufacturing a Blading Component
Stator Vane for 3D Composite Blower
Ring Sector of Turbomachine Turbine
Turbomachine Optimized for Fastening a Rotary Shaft Bearing. a Method of Mounting Said Bearing on Said Turbomachine
Method for Digitizing an Analogue Signal with an Analogue-Digital Converter of Determined Shannon Frequency
Method for Detecting Resonance in a Rotor Shaft of a Turbine Engine
Fuel Injection System for a Combustion Chamber of a Turbomachine
Structural and Aerodynamic Module for a Turbomachine Casing and Casing Structure Comprising a Plurality of Such a Module
Airfoil Attachment Holding an Airfoil Root in a Broach Fitting
Method of Repairing or Reworking a Turbomachine Disk and Repaired or Reworked Turbomachine Disk
Method for Increasing the Coefficient of Adhesion Between Two Parts Rotating as One with a Rotor
Method of Determining the Conditions of a Phase for Machining a Workpiece with Modulated Cutting Rate
Vibration Damper Device for Turbomachine Blade Attachments, Associated Turbomachine and Associated Engines
Inner Wall for a Turbomachine Nacelle
Fixed Vane Assembly for a Turbine Engine Having a Reduced Weight, and Turbine Engine Comprising at Least One Such Fixed Vane Assembly
Method of Polishing Bladed Disks for a Turbomachine and Polishing Device
Device for Attaching a Flame-Holder Arm to an Afterburner Housing
High-Pressure Turbine for Turbomachine, Associated Guide Vane Sector and Aircraft Engine
Stationary Vane Assembly for a Turbine Engine Having a Reduced Weight, and Turbine Engine Comprising at Least One Such Stationary Vane Assembly
Compressor Housing Resistant to Titanium Fire, High-Pressure Compressor Including Such a Housing and Aircraft Engine Fitted with Such a Compressor
Method for the Manufacture of a Circular Revolution Thermomechanical Part Including a Titanium-Based Load-Bearing Substrate Lined with Steel or Superalloy, a Turbomachine Compressor Housing Which Is Resistant to Titanium Fire Obtained According to This Method
Airplane Having Engines Partially Encased in the Fuselage
Method and a Device for Detecting an Electrical Failure Affecting an Electric Control System of a Hydraulic Actuator of Variable Geometries of an Aeroengine
Piston with a Duct Under a Gasket
Feathering Device for the Fan Blades of a Turboprop Engine
Stator Stage for Turbomachine Compressor
Rotor for a Gas Turbine Engine Comprising a Rotor Spool and a Rotor Ring
Closed-Circuit Installation for the Surface-Treatment of Components in a Liquid Bath
Suspension Rudder Bar for an Aircraft Turbojet and a Suspension with Fan Hanger Provided Therewith
Fuel Feed Device for Aviation Engine
Turbomachine Casing
Circuit and a Method for Feeding Oil to Rolling Bearings in a Turbomachine
Method and System for Lubricating a Turbine Engine
Assembling Titanium and Steel Parts by Diffusion Welding
Method and System for Monitoring a Turbojet Engine
System for Controlling Variable Geometry Apparatuses in a Turbine Engine
System for Controlling Variable Geometry Equipment of a Gas Turbine Engine Especially Comprising a Guiding Track Connection
System for Controlling Variable Geometry Equipment for a Turbine Engine, Especially by Bellcranks
System for Controlling Variable Geometry Equipment of a Gas Turbine Engine Particularly Comprising a Barrel Link
Sealing Between a Combustion Chamber and a Turbine Nozzle in a Turbomachine
Turbine Blade with Improved Aerodynamic Performance
Ventilation of a High-Pressure Turbine in a Turbomachine
Turbine Blade Equipped with Means of Adjusting Its Cooling Fluid Flow Rate
Oil-Separator Rotor for a Turbomachine
Counting Inclusions in Alloys by Image Analysis
Computer Aided Design Method for Creating a Surface in a Complex System
Annular Flange for Fastening a Rotor or Stator Element in a Turbomachine
Air Inlet of an Aeroengine Having Unducted Pusher Propellers
Detection of Anomalies in an Aircraft Engine
Anti-Wear Device for the Blades of a Turbine Distributor in an Aeronautical Turbine Engine
Composite Material Turbine Engine Vane, and Method for Manufacturing Same
Method for Manufacturing a Complexly Shaped Composite Material Part
Turbine Engine Fan Comprising a Balancing System with Blind Holes for Accommodating Masses
Method for Smoothing the Surface of a Part Made from a Cmc Material
Method and System for Correcting a Temperature Measurement Signal
Estimating a Stream Temperature in a Turbojet
Seal for a Platform in the Rotor of a Turbine Engine
System of Contra-Rotating Propellers Driven by a Planetary Gear Train Providing a Balanced Distribution of Torque Between the Two Propellers
Standardizing Data Used for Monitoring an Aeroengine
Identifying Failures in an Aeroengine
Method for Manufacturing a Turbine Engine Vane
Device for Attaching Hammer Clamp Blades, Associated Compressor Hub, Compressor and Turbine Engine
Turbine Engine Rotor Wheel with Blades Made of a Composite Material Provided with a Spring Ring
Compressor Casing with Optimized Cavities
Method for the Non-Destructive Inspection of a Mechanical Part
Device for Injecting a Mixture of Air and Fuel into a Turbomachine Combustion Chamber
Device for Measuring the Twist of a Rotating Shaft
Variable-Pitch Vane for Stator Stage, Including a Non-Circular Inner Platform
Method and a System for Monitoring Vibratory Phenomena That Occur in an Aviation Gas Turbine Engine in Operation
Diffuser/Rectifier Assembly for a Turbine Engine with Corrugated Downstream Walls
System of Compact Contra-Rotating Propellers
Method of Repairing a Flange of a Casing
Method of Machining Rotor Blade Wear Indicators, and Rotor Blade Plug for Implementing the Method
Control of Axial Thrust by Guidance of the Air Drawn Off from a Centrifugal Compressor
Cooling Device for Cooling the Slots of a Turbomachine Rotor Disk Downstream from the Drive Cone
Device for Monitoring the Obstruction of at Least Two Filters of a Fluid Circulation System of an Aircraft Gas Turbine Engine
Bleeding of Air via the Diffuser of a Centrifugal Compressor of a Turbine Engine
Turbine Stage
Optimized Aerodynamic Profile for a Turbine Blade, in Particular for a Rotary Wheel of the Third Stage of a Turbine
Optimized Aerodynamic Profile for a Turbine Vane, in Particular for a Nozzle of the Third Stage of a Turbine
Device for Heating a Cylindrical Component and Use in Assembling an Inter-Shaft Bearing in a Turbomachine
Optimized Aerodynamic Profile for a Turbine Vane, in Particular for a Nozzle of the Fourth Stage of a Turbine
Optimized Aerodynamic Profile for a Turbine Blade, in Particular for a Rotary Wheel of the Second Stage of a Turbine
Optimized Aerodynamic Profile for a Turbine Vane, in Particular for a Nozzle of the Second Stage of a Turbine
Optimized Aerodynamic Profile for a Turbine Blade, in Particular for a Rotary Wheel of the First Stage of a Turbine
Optimized Aerodynamic Profile for a Turbine Blade, in Particular for a Rotary Wheel of the Fourth Stage of a Turbine
Turbine Engine with Nonstreamlined Impellers
Turbojet Engine with an Element of the Nacelle Attached to the Intermediate Casing
Assembly Between a Compressor Shaft Trunnion and a Bevel Gear for Driving an Accessory Gearbox of a Turbomachine
Rotor Blade of a Gas Turbine Engine Made of Composite Material Comprising a Connecting Yoke, Method for Manufacturing the Blade
Retaining Ring
Lubricating and Cooling Epicyclic Stepdown Gearing
Aeronautical Engine with Cooling of an Electric Starting Device
Method and System for Controlling a Gas Turbine and a Gas Turbine Including Such a System
Turbojet Nacelle Having a Removable Air Intake Structure
Device with Counter-Rotating Propellers Having a Propeller Pitch Altering Means
Gas Turbine Engine Having Fan Blades of Adjustable Pitch with Cyclic Setting
Rotor Element with a Fluid Passage and Passage-Blocking Member and Turbine Engine Including the Rotor Element
Monitoring Particles in a Lubrication System
Circumferential Blocking Device of Clamp Vanes for Turbine Engine, with Improved Radial Deployment
Bushing for a Variable Set Blade
Propeller and System of Counter-Rotating Propellers Comprising Improved Means for Limiting Pitch, and a Turbine Engine Comprising Them
Bellows Type Sealing Device for Partition Penetration by a Connecting Rod of a Turboprop Fan Blade Orientation Control System
Method and Device for Machining the Leading Edge of a Turbine Engine Blade
Suspension for an Engine on an Aircraft Strut Including a Suspension Arch
Device for Repairing the Casing Holder of an Aeronautical Engine
Drive Mechanism for a Pair of Contra-Rotating Propellers Through an Epicyclic Gear Train
Turbomachine Combustion Chamber Comprising Improved Means of Air Supply
Engine and Pod Assembly for an Aircraft, Equipped with an Anti-Icing Device Including a Source of Radiation and Pulse Control Unit Connected to the Source of Radiation
Disengageable Axial Abutment
Turbine Vane with Dusting Hole at the Base of the Blade
Contactless Electrical Connector for an Induction Sensor, and Sensor Including Such a Connector
Workshop for Preparing Aircraft Engines for Shipping
Elbow Bracket for Aeronautical Equipment
Unducted Fan with Variable-Pitch Blades for a Turbine Engine
Double-Body Gas Turbine Engine Provided with an Inter-Shaft Bearing
Device for Fueling Launcher Thrusters
Process for Smoothing the Surface of a Part Made of Cmc Material
Device for Separating the Two Portions of a Launcher Refueling Module
Rotating Inlet Cowl for a Turbine Engine, Comprising an Eccentric Forward End
Method for Manufacturing an Assembly Including a Plurality of Blades Mounted in a Platform
Reinforced Fan Blade Shim
A Sealing Head for an Installation for Fluid Tests on an Aircraft Turbine Engine Part
Mixing Screw for a Fuel Injector in a Combustion Chamber of a Gas Turbine, and Corresponding Combustion Device
Shell for Aircraft Turbo-Engine Stator with Mechanical Blade Load Transfer Slits
Device for Acoustic Treatment of the Noise Emitted by a Turbojet
Process for Depositing a Coating for Protection Against Oxidation and Against Hot Corrosion on a Superalloy Substrate
Device for Spacing Electrical Harnesses in a Turbomachine
Aeroengine Fan Casing Made of Composite Material, and a Method of Fabricating It
Method and a Device for Monitoring a Servo-Control Loop of an Actuator System for Actuating Variable-Geometry Components of a Turbojet
Blade Retention Disk
Sealing System with Annular Brush Seal
Low Pressure Turbine for an Aircraft Turbomachine, Comprising a Segmented Nozzle with an Improved Design
System for Detecting an Ephemeral Event on a Vane Impeller of an Aircraft Engine
Turbomachine Rotor with Anti-Wear Shim Between a Disk and an Annulus
Pylon for Fixing an Aircraft Engine Having Unducted Pusher Propellers
Turbojet Including an Automatically Variable Flow Rate Bleed Circuit for Cooling Air
Method and Device for Feeding a Turbomachine Combustion Chamber with a Regulated Flow of Fuel
Fan Rotor for an Airplane Turbojet
Unducted Propeller with Variable Pitch Blades for a Turbomachine
Hall Effect Plasma Thruster with Insulated Layered Ring Assembly
Turbomachine Nozzle Cowl Having Patterns with Lateral Fins for Reducing Jet Noise
Low-Pressure Turbine
A Method and a Device for Coating Ceramic Material Fibers in Metal by a Liquid Technique
Device for Controlling the Pitch of Fan Blades of a Turboprop
Method for Manufacturing a One-Piece Annular Metal Part Having a Reinforcing Insert of Composite Material
Tooling and a Method for Hot Forging Pieces of Sheet Metal
Compressor Nozzle Stage for a Turbine Engine
Control Unit and a Method for Controlling Blade Tip Clearance
Method of Producing a Guide Vane
Method and Device for Determining the Capacity of an Aircraft Pump to Deliver a Predetermined Fuel Output
Stationary Actuator Device for Controlling the Pitch of Fan Blades of a Turboprop
Movable Actuator Device for Controlling the Pitch of Fan Blades of a Turboprop
Turbine Engine Including an Improved Means for Adjusting the Flow Rate of a Cooling Air Flow Sampled at the Output of a High-Pressure Compressor Using an Annular Air Injection Channel
Device and Method for Detecting a Fault in a Low-Pressure Fuel Pump of a Turbojet and Turbojet Including One Such Device
Bench and a Method for Magnetoscopically Testing a Turbine Engine Shaft
Method of Testing a System for Protecting a Turbomachine Against Overspeed While Starting
Nondestructive Test of a Sealing Member
Device for Checking a Turbomachine Engine
Device and Method for Positioning Variable-Geometry Equipment for a Turbomachine, Using a Relative-Measurement Jack
Method for Manufacturing a Forged Part with Adaptive Polishing
Application:
13/380,988 →
Publication:
US 2012/0124834
Device for the Nondestructive Test of a Part
Propeller Hub
Method for Producing Martensitic Steel with Mixed Hardening
Cryogenic Treatment of Martensitic Steel with Mixed Hardening
Deoiler Layout
Method and System for Controlling Aircraft Engine Starter/Generator
Beam for Suspending a Turboshaft Engine from an Aircraft Structure
Method of Fabricating a Thermal Barrier
Part Comprising a Substrate Carrying a Ceramic Coating Layer
Prestressing Device Having Radial Activity
Combustion Chamber for a Turbomachine Including Improved Air Inlets
Prestressing Device Having Circumferential Activity
Optimised Manufacturing Process for a Vaned Monobloc Disc by Abrasive Water Jet
Vibration-Damping Shim for Fan Blade
Optimised Manufacturing Process for a Vaned Monobloc Disc by Abrasive Water Jet
Hub for a Propeller Having Variable Pitch Blades
A Method of Detecting Contamination of Titanium Alloys of Two-Phase Type Having an Alpha and a Beta Phase
Turbine Engine Compressor Having Air Injections
Controlling Blade Tip Clearances in a Turbine Engine
Method for the Detection of Failures in a Turbomachine by Means of a Theoretical Model of the Thermodynamic Cycle of the Said Turbomachine
Prediction of Maintenance Operations on an Aircraft Engine
Multipoint Injector for Turbomachine
Porous Core Cowling for a Turbojet Engine
Application:
13/434,163 →
Publication:
US 2012/0247083
Cmc Turbine Nozzle Adapted to Support a Metallic Turbine Internal Casing by an Axial Contact
Cmc Turbine Nozzle Adapted to Support a Metallic Turbine Internal Casing by a Radial Contact
Turbine Wheel for a Turbine Engine
Turbine Engine Fan Disk
System for Securing Two Tubular Components One in the Other, Carrying a Roller Bearing
Suspension Rods for the Bypass Flow Duct of a Turbojet with Eccentric Ball Joints
Process for the Vapor Phase Aluminization of a Turbomachine Metal Part and Donor Liner and Turbomachine Vane Comprising Such a Liner
Hall-Effect Plasma Thruster
Turbine Engine with Contra-Rotating Non-Ducted Propellers
Method for Forming a Protective Coating Containing Aluminum on the Surface of a Metal Part
Part Comprising a Structure and a Shape Memory Alloy Element
Combustion Chamber of an Aeronautical Turbine Engine with Combustion Holes Having Different Configurations
Method of Fabricating a Turbine Engine Blade Out of Composite Material
Rotor of a Turbomachine Compressor, with an Optimised Inner End Wall
Method of Lost-Wax Manufacture of an Annular Bladed Turbomachine Assembly, Metal Mould and Wax Model for Implementing Such a Method
Repairing Titanium Compressor Blades by Cold Compacting
Device for Centering and Guiding the Rotation of a Turbomachine Shaft
System for Controlling the Angular Position of Stator Blades and Method for Optimizing Said Angular Position
A Fuel Feed Circuit for an Aeroengine Having a High Pressure Pump System with Two Pumps
Fuel Feed Circuit with Hydraulic Actuator and Fuel Meterng Unit for an Aeroengine
Homogenization of Martensitic Stainless Steel After Remelting Under a Layer of Slag
Multipoint Injector for a Turbine Engine Combustion Chamber
Multipoint Injection Device for a Combustion Chamber of a Turbine Engine
Degassing of Martensitic Stainless Steel Before Remelting Beneath a Layer of Slag
Heat Treatment of Martensitic Stainless Steel After Remelting Under a Layer of Slag
Gas Turbine Engine Air Intake in a Nacelle
System for Varying the Angle of Attack of the Blades of an Aircraft Turbine Engine Propeller, Using a Brushless Electric Motor
Fuel Mixing Device for Turbine Engine Combustion Chamber Comprising Improved Air Feed Means
Dual-Flow Turbomachine for Aircraft, Including Structural Means of Rigidifying the Central Casing
Device and Method for Recovering Magnetic Particles Trapped on a Magnetic Plug
Metallic Annular Connection Structure for Aircraft Turbomachine
Turbo Machine Electrical Connection Element
Method for Detecting Damage in at Least One Engine Roller Bearing
Aircraft Engine Module Handling Assembly
Device for Changing the Transmission Ratio Between a Turbine Shaft and a Shaft of a Starter-Generator of an Aeroengine
Mounting an Agb on an Intermediate Casing for a Turbojet Fan Compartment
Combustion Chamber Having a Ventilated Spark Plug
System and Method for Measuring Fatigue for Mechanical Components of an Aircraft and Aircraft Maintenance Method
Carriage for Transport of an Aircraft Engine Module
Insulating a Circumferential Rim of an Outer Casing of a Turbine Engine from a Corresponding Ring Sector
Turbine Engine Having a Stage of Variable-Pitch Stator Vanes with Independent Control
Method and a Device for Real Time Monitoring of a System for Measuring a Fuel Flow Rate
Method for Repairing a Titanium Blade by Laser Recharging and Moderate Hip Pressing
Application:
13/512,054 →
Publication:
US 2012/0276304
Method for Manufacturing a Straight Insert Made of Metal Matrix Composite Material
Method and Device for Monitoring Torsional Vibrations of a Rotary Shaft of a Turbine Engine
Guiding a Sparkplug in a Turbine Engine Combustion Chamber
Retaining Ring Assembly and Supporting Flange for Said Ring
Propeller Hub Having a Reinforced Polygonal Ring and Turbine Engine Provided with Such a Hub
Combustion Chamber for a Turbine Engine
Turbine Engine Turbine Blade Made of a Ceramic-Matrix Composite with Recesses Made by Machining
Method of Fabricating Inconel 718 Type Nickel Superalloys
Application:
13/514,891 →
Publication:
US 2012/0247626
Heat Exchanger for a Hot Fuel Cell
Endoscope-Like Adjustable Structure
Aircraft Propeller Blade
Method for Producing a Metal Reinforcement for a Turbine Engine Blade
Inner Ventilation Blade
Application:
13/519,339 →
Publication:
US 2012/0282110
Method and an Assembly for Electrolytically Depositing a Coating
Contra-Rotating Propeller System for an Aircraft Turbine Engine
High-Pressure Turbine Nozzle for a Turbojet
Diffuser-Guide Vane Connection for a Centrifugal Compressor
Turbine engine blade
Method of Controlling Speed Transients in a Turbine Engine
Device for Controlling the Pitch of Turboprop Fan Blades
Fluidic Dampening Film Supply Method for a Guiding Bearing of a Turbine Engine Shaft
Method for Monitoring a Pressure Relief Valve of a Fuel Injection Circuit for a Turbomachine
Turbojet engine case, notably intermediate case
Application:
13/557,722 →
Publication:
US 2013/0202425
Turbojet Engine Fan Duct Suspension Using Connecting Rods with Elastomer Bushing
Method of Using Laser Shock Impacts to Produce Raised Elements on a Wall Surface Capable of Being Swept by a Fluid in Order to Control the Intensity of Turbulence in a Transition Zone
Method of Fabricating a Composite Material Blade Having Internal Channels, and a Composite Material Turbine Engine Blade
Uncoupling System for an Aircraft Turbojet Engine Rotary Shaft
Means for Locking a Sealing Ring on a Turbine Disk
Turbine Engine Fan
Cutting of Preforms Prior to Rtm Injection by Means of a Water Jet and Cryonics
Method for the Automated Detection of the Ingestion of at Least One Foreign Body by a Gas Turbine Engine
Method for Repairing a Flange of a Housing
Link Between the Exhaust Casing and a Structural Ring of the Fan Duct of a Jet Engine
Method and a Device for Correcting a Measurement of the Pressure of a Gas Stream Flowing in an Aircraft Engine
Device for Obtaining Ceramic Fibers Coated by a Liquid Process with a Thick Metal Sheath
Assembly Having a Control Device with Racks for Controlling the Angular Position of Pivotally-Mounted Blades in a Turbine Engine
Circuit for Detecting the Positions of Contactors in a Turbine Engine
Turboprop Provided with a Blade-Positioning Device
Injection System for a Turbomachine Combustion Chamber, Including Air Injection Means Improving the Air-Fuel Mixture
Device for Reducing Noise from Jet-Pylon Interactions on Jet Engines
Fiber Preform for a Turbine Ring Sector, and Its Method of Fabrication
Mounting for Locking a Vane by Means of the Blade Thereof During Machining of the Root of Said Vane
Counterweight-Based Device for Controlling the Orientation of Fan Blades of a Turboprop Engine
Mechanical Transmission Device for Driving in Rotation Counter-Rotating Propellers of a Dual-Propeller Turboprop
Device for Activating a Passive Ejector Valve for Pressurising a Turbojet Engine Chamber for an Aircraft
Soundproofing Panel for Turbomachine and Turbomachine Comprising Such a Panel
Turbojet Engine Outlet Lobe Mixer with Guiding Protrusions, and Method of Mixing Airflows
Turbomachine Blades or Vanes Having Complementary Even/Odd Geometry
Turbomachine Blade or Vane Having Complementary Asymmetrical Geometry
Composite Material Turbomachine Engine Blade or Vane, Compressor Stator Segment or Turbine Nozzle Segment Incorporating Such Vanes and Method for Manufacturing Same
Method for Monitoring at Least Two Temperature Sensors of a Turbomachine
Method for Determining a Zone Where a Combustion Chamber Ignition Plug Is to Be Positioned, and Associated Combustion Chamber
Method for Manufacturing a Thermal-Barrier Protection and Multilayer Coating Suitable for Forming a Thermal Barrier
Mechanism for Variable Adjustment of Blades for a System of Contra-Rotating Propellers, and a System of Contra-Rotating Propellers Comprising at Least One Such Mechanism
Method for Producing a Metal Insert to Protect a Leading Edge Made of a Composite Material
Turbojet Venting Pipe, Method for Mounting One Such Pipe and Turbojet Provided with One Such Pipe
Turboshaft Engine Supporting Pylon Covered with a Porous Material and Turboshaft Engine/Pylon Assembly
Turbomachine Combustion Chamber Having a Perforated Chamber End Wall and with No Deflector
Device and Method for Recovering Magnetic Particles Trapped on a Magnetic Plug
Sealing Device for Jet Engine Oil Chamber
Method of Manufacturing an Elongate Insert Made of a Metal Matrix Composite
Device and Process for Controlling the Efficiency of a Metal Electrodeposition Bath
Application:
13/637,854 →
Publication:
US 2013/0008797
Engine Compressor, Particularly Aircraft Jet Engine Compressor, Fitted with an Air Bleed System
Method of Analyzing a Plurality of Ferromagnetic Particles
Wear-Resistant Part for the Support of a Blade of a Turbojet Fan
Unducted Fan for Turbine Engine
Device for Measuring Temperature in a Primary Stream Flow Passage of a Bypass Turbojet
Method and a Device for Producing a Setpoint Signal
Flow Straightener Device for Turbomachine
Method and System for Monitoring the Level of Oil Contained in a Tank of an Aircraft Engine
Device for Manufacturing a Casing Made of a Composite Material and Manufacturing Method Using Such a Device
Device Evaluating Thermomechanical Fatigue of a Material
Tooling for Injection-Molding a Part
Removable Mask for a Turbomachine Blade or Distributor Sector Platform
Hall-Effect Motor in Which the Temperature of the Cathode-Heating Device Is Controlled
Method of Processing Acoustic Waves Emitted at the Outlet of a Turbo Engine of an Aircraft with a Dielectric-Barrier Discharge Device and Aircraft Comprising Such a Device
Interface Element Between a Blade Root and a Blade Root Housing of a Turbine Disc, and Turbine Rotor Comprising an Interface Element
Turbine Engine Comprising a Contrarotating Propeller Receiver Supported by a Structural Casing Attached to the Intermediate Housing
Turbomachine Blade Incidence Control System and Turbomachine
Turbine Wheel for a Turbine Engine
Method for Mounting a Stator Blading of a Turbomachine, an Engine Casing and a Turbomachine Comprising at Least One Stator Blading Mounted on This Engine Casing
System for Controlling a Pneumatic Valve of a Turbine Engine
Application:
13/669,999 →
Publication:
US 2013/0115055
An Airplane Including Means for Taking at Least a Portion of the Boundary Layer of the Flow of Air Over a Surface
Method for Monitoring the Clearance of a Kinematic Link Between a Control Member and a Receiving Member
Annular Casing for a Turbine Engine Compressor
Method for Monitoring a Control Device of a Fuel Metering Valve of a Turbojet Engine
Cooled Turbine Blade for Gas Turbine Engine
Device for Injection-Moulding a Part
Aerodynamic Coupling Between Two Annular Rows of Stationary Vanes in a Turbine Engine
Device for Reducing the Noise Emitted by the Jet of an Aircraft Propulsion Engine
Gas Turbine Engine Rotor Wheel Having Composite Material Blades with Blade-Root to Disk Connection Being Obtained by Clamping
Multi-Layer Acoustic Treatment Panel
Method for Determining the Torque and/or Angular Speed of a Rotating Shaft and a Device for Carrying Out Same
Vortex Generators for Generating Vortices Upstream of a Cascade of Compressor Blades
Method of Non-Destructive Inspection and a Device for Implementing the Method
Gearbox in a Turbine Engine
Application:
13/699,949 →
Publication:
US 2013/0104681
Measuring the Damage to a Turbine-Blade Thermal Barrier
Turbo Machine with a Device for Preventing a Segment of Nozzle Guide Vanes Assembly from Rotating in a Casing; Rotation-Proofing Peg
Rolling Bearing for Aircraft Turbojet Fitted with Improved Means of Axial Retention of Its Outer Ring
Preheating a Spark Plug
Application:
13/701,850 →
Publication:
US 2013/0125558
Fibrous Structure Forming a Flange and a Counter-Flange
Method for Manufacturing an Article Made of Composite Material
Compressor and a Turbine Engine with Optimized Efficiency
Turboshaft Engine Attached to a Pylon of the Fuselage of an Aircraft by a Failsafe Suspension System
Guide and Sealing Device for a Turbine Engine, the Device Having a Carbon Gasket and an Integrated Smooth Bearing
Blade Having an Integrated Composite Spar
Arrangement for the Guiding of the Flow of a Liquid in Relation to the Rotor of a Turbomachine
Method for Monitoring a Fuel Circuit Shut-Off Valve
Device for Fuel Return Valve
Safety Device for Controlling an Engine Comprising Acquisition Redundancy of a Sensor Measurement
System for Detecting an Impact on an Aircraft Engine Impeller Wheel
Gas Turbine Engine Fan Casing Having a Flange for Fastening Pieces of Equipment
Annular Anti-Wear Shim for a Turbomachine
Axisymmetric Part for an Aviation Turbine Engine Rotor
Method for Defining the Shape of a Turbomachine Convergent-Divergent Nozzle, and Corresponding Convergent-Divergent Nozzle
Method for Measuring the Deformation of a Turbo-Machine Blade During Operation of the Turbo-Machine
Propulsion Assembly and Method
Device for Lubricating an Epicycloidal Reduction Gear
System for Detecting the First Signs of a Malfunction of an Aircraft Engine Valve
System for Detecting Defects on an Aircraft Engine Impeller Wheel
Method for Producing a Metal Reinforcement for a Turbomachine Blade
Angular Sector of a Stator for a Turbine Engine Compressor, a Turbine Engine Stator, and a Turbine Engine Including Such a Sector
Method of Detecting a Fault with the Means for De-Icing a Probe for Measuring a Physical Parameter
Method for Aluminizing a Surface by Means of the Advance Deposition of a Platinum and Nickel Layer
Angular Sector of a Stator for a Turbine Engine Compressor, a Turbine Engine Stator, and a Turbine Engine Including Such a Sector
Process for Manufacturing a Metal Part by Selectively Melting a Powder
Procedure for Igniting a Turbine Engine Combustion Chamber
Process for Forming a Protective Coating on the Surface of a Metal Part
Method and Device for Detecting a Rotational Separation Adversely Affecting a Turbine Engine Compressor
Method for Producing a Solid Part
Inter-Blade Sealing for a Turbine or Compressor Wheel of a Turbine Engine
Fuel Injection System for Turbojet Engine and Method of Assembling Such an Injection System
Lateral Turbojet Improved in Order to Limit the Deformation Thereof
Method of Fabricating a Turbine Engine Drum
Device for Locking a Root of a Rotor Blade
Electric Thruster, a Method of Stopping an Electric Engine Included in Such a Thruster, and a Satellite Including Such a Thruster
Detection of the Ingress of Water or Hail into a Turbine Engine
Combustion Chamber for an Aircraft Engine, and Method for Attaching an Injection System in a Combustion Chamber of an Aircraft Engine
Aerodynamic Shroud for the Back of a Combustion Chamber of a Turbomachine
Hyperstatic Truss Comprising Connecting Rods
Connecting Module Between a Drive Shaft of an Engine Fan and a Rolling-Element Bearing
Martensitic Stainless Steel Machineability Optimization
Sealing Device Having a Sleeve for the Passage of a Connecting Rod of a System for Controlling the Orientation of the Blower Blades of a Turboprop Engine Through a Partition
System for Pressuring the Bearing Chambers of Turbine Engines Machines Using Air Taken from the Intake Duct
Gas Turbine Engine Comprising Means for Axially Retaining a Fan of the Engine
Mold for Producing Parts by Wax Injection
Device for Uncoupling a Bearing Carrier
Method of Fabricating a Part and a Composite Solid Part Obtained by the Method
Injection Mold for a Wax Model of a Turbine Blade Having an Isostatic Core Holder
Equipment Comprising a Rotatable Cradle and Intended for Encasing the Airfoil of a Turbine Blade in Order to Machine the Root
Device for Injecting a Mixture of Air and Fuel into a Turbine Engine Combustion Chamber
Nose Dome for a Turbomachne Blower
System for Attaching a Turbojet Engine Spinner
Method of Designing a Multi-Stage Turbomachine Compressor
Patent:
9,482,237 →
Application:
13/850,755 →
Method for Managing the Operation of a Fuel Metering Unit
A Compressor Guide-Vane Stage for a Turbine Engine Including a Gasket Between a Vane and a Shroud of the Guide-Vane Stage
Method for Manufacturing a Turbine Engine Part by Injection of Resin Under Pressure
Spark Plug for Combustion Chamber of a Gas Turbine Engine
Hydraulic Device of a Control Device, Such as a Blade Pitch-Change Device
Method for Producing a Metal Reinforcement for a Turbomachine Blade
Method for Manufacturing a Metal Part
Monitoring System for an Engine Test Bench
Method for Producing a Fibrous Metal Structure by Means of Weaving
Hydraulic Device for Changing the Pitch of a Propeller
Method and a Device for Monitoring a Servo-Control Loop of an Actuator System for Actuating Variable-Geometry Components of a Turbojet
Control of a Fuel Metering Device for Turbomachine
Method of Controlling a Turbomachine
Set of Rotor Disks for a Turbine Engine
Method for Machining a Casing of an Aircraft Turboshaft Engine and Scraper Tool for Implementing Said Method
Device for Shifting a Propeller into Reverse, Comprising an Actuator Acting on a Crank Pin
Monitoring of a Filter of the Fuel-Supply System of an Aircraft Engine
Device for Measuring Vibration Amplitudes of the Blade Tips in a Turbomachine
Spacer Interposed Between a Blade Root and the Bottom of a Slot in the Disk in Which the Blade Is Mounted
Reduction Gear with Epicyclic Gear Train Having Roller-Bearing-Mounted Planet Spindles
Method of Fabricating a Part by Selective Melting or Selective Sintering of Powder Beds by Means of a High Energy Beam
Turbine wheel in a turbine engine
Casting Method for Obtaining a Part Including a Tapering Portion
Method of Determining the Breaking Stress in Shear of a Part of Determined Thickness
Application:
13/917,227 →
Publication:
US 2013/0345992
Method of Synchronizing Data for Algorithms of Asynchronous Computers of an Aircraft
Interblade Platform for a Fan, Rotor of a Fan and Associated Manufacturing Method
Application:
13/926,316 →
Publication:
US 2014/0003949
Hub for Radial Housing of a Helical Ring of a Turbomachine with Variable-Pitch Blades and Assembly Comprising Such a Hub
Turbomachine with Variable-Pitch Vortex Generator
Parts Assembled Through Friction Welding
Composite Material Part Having Thermal Protection Based on Resin, and Its Method of Fabrication
Valve for Controlling Heat Exchanges in an Oil Circuit
Device for the Blind Coupling of Fluidic, Electrical or Similar Supplies, to a Receiving Control Mechanism
Method of Carrying Out a Vibratory Fatigue Test of a Mechanical Part
A Martensitic Steel with Mixed Hardening
Labyrinth Disk for a Turbomachine
Method of Sticking Together and Un-Sticking Two Parts by Means of a Filled Adhesive
Method for Balancing a Turbomachine Rotor
Composite Turbine Engine Blade with Structural Reinforcement
Discharge System of a Separated Twin-Flow Turbojet for an Aircraft, Corresponding Turbojet and Associated Design Method
Axisymmetrical Intermediate Case Part Including an Insert Positioned in an Annular Groove
Chamber-Bottom Baffle, Combustion Chamber Comprising Same and Gas Turbine Engine Fitted Therewith
Test Systems and Processes for Equipment Vis-a-Vis Contaminated Fuel
Method for Assembling a Nozzle and an Exhaust Case of a Turbomachine
Device for Suspending a Turbojet Engine
Bypass Turbojet
Fuel Circuit for an Aviation Turbine Engine, the Circuit Having a Fuel Pressure Regulator Valve
Method of Making a Piece of Metal Reinforcement
Method for Disconnecting, by Induction, a Magnetic Mechanical Part Adhered to a Mechanical Part
Multilayer Woven Fibrous Structure Including a Hollow Tubular Part, Production Method Thereof and Composite Part Comprising Same
Fibrous Structure for a Part Made of a Composite Material and Having a Complex Shape
Method of Making a Metal Reinforcing Piece
Injection Device for a Turbine Engine Combustion Chamber
Method for Perforating a Wall of a Combustion Chamber
Sintering and Laser Fusion Device, Comprising a Means for Heating Powder by Induction
Fan Rotor and Associated Turbojet Engine
Reduced Pressure-Drop Pipe Element
Airfoil and Platform Assembly for Supersonic Flow
Airfoil and Platform Assembly for Subsonic Flow
Composite Material Part Comprising Fixing Means
Method for Controlling the Clearance at the Tips of Blades of a Turbine Rotor
Monitoring of an Aircraft Engine for Anticipating Maintenance Operations
Valve
Movable Blade for a Turbomachine
Oil Discharge Device and Turbomachine Comprising Such a Device
Combined Turbojet and Ramjet Engine
Turbine Engine Blade Having Improved Stacking Law
Fibrous Structure for a Part Made of Composite Material Having One or More Archshaped Portions
Device for Searching for Defects on Parts by Endoscopy
Three-Port Valve
Driveshaft for the Gearbox of Auxiliary Machines of a Turbojet Engine
Method for Manufacturing a Metal Part
Annular Combustion Chamber for a Turbine Engine Including Improved Dilution Openings
Process for Making a Metal Part Such as a Turbine Engine Blade Reinforcement
Process for Manufacturing a Metal Part, Such as Turbine Engine Blade Reinforcement
Method for Manufacturing an Integral Rotationally Symmetrical Metal Part Including a Reinforcement Consisting of Ceramic Fibers
Method for the Elimination of Rotational Stall in a Turbine Engine
Pipe Having an Upstream Core Having a Sharp Curvature
Process for Producing a Thermal Barrier in a Multilayer System for Protecting a Metal Part and Part Equipped with Such a Protective System
Method and Device for Monitoring a Servovalve Actuation System
Process for Local Repair of a Damaged Thermomechanical Part and Part Thus Produced, in Particular a Turbine Part
Turbine Casing Comprising Ring Sector Attachment Means
Method for Monitoring the Change in State of a Valve by Measuring Pressure
Process for Manufacturing a One-Piece Axisymmetric Metallic Part from Composite Fibrous Structures
Turbomachine with Fan(S) for Aircraft, with Mobile Jet Nozzle
Installation for Non-Destructive Testing, by Immersion Ultrasounds, of Workpieces
Method for Optimizing the Speed of a Twin-Spool Turbojet Engine Fan, and Architecture for Implementing Same
Method of Inspecting Impacts Observed in Fan Casings
System for Changing the Pitch of the Contra-Rotating Propellers of a Turboshaft Engine
Device for Suspending a Turbine Engine from an Airplane
Sealing Ring for a Turbine Stage of an Aircraft Turbomachine, Comprising Slotted Anti-Rotation Pegs
Fuel Circuit Comprising Means for Controlling a Pump
Epicycloidal Measurement Shaft
Mixer That Performs Reciprocating Rotary Motion for a Confluent-Flow Nozzle of a Turbine Engine, and a Method of Controlling It
Injection Device for a Combustion Chamber of a Turbine Engine
Method and Device for Determining the Air Bleed on an Aircraft Turbojet Engine
Cleat for Open-Work Blade Foot
Turbomachine Propeller Blade Setting Device
Propeller Comprising a Counterweight System Provided with an Air Discharge Channel
Measurement Installation for Blade Failure Testing in a Turbomachine
Method to Improve the Thermal Properties of a Resistance Element Embedded in an Alumina Deposit on a Surface of a Substrate and Application of Said Method
In-Line Removable Heat Shield for a Turbomachine Suspension Yoke
High-Pressure Turbine Blades Made of Ceramic Matrix Composites
Method of Constructing a Behavior Model of an Airplane Engine
Combustion Chamber for a Turbine Engine
Customers Comparison and Targeting Method
Application:
14/084,875 →
Publication:
US 2015/0142559
Device for Supplying and Distributing Fluid
Sealing of Turbine Engine Enclosures Produced by Brush Seal and Labyrinth
Guidance of Turbine Engine Shafts
Vibration Dampening Device for the Manufacture of a Rotor
Device for De-Icing a Leading Edge of a Turbine Engine by Slanting Notches
Fuel Circuit of a Turbine Engine
Method for Mounting an Aircraft Engine on a Pylon, and Engine Fastener for Implementing Said Method
Compacting Device for a Machine for Winding a Fibrous Texture Onto an Impregnation Mandrel
Machine for Winding a Fiber Texture Onto an Impregnation Mandrel, and the Use of Such a Machine for Making a Gas Turbine Casing Out of Composite Material
Propulsion Device Having Unducted Counter-Rotating and Coaxial Rotors
Assembly Comprising a Protection Device and a Turbine Machine Element for Protecting
Aircraft Engine Annular Shroud Comprising an Opening for the Insertion of Blades
Turbine Engine Comprising a Metal Protection for a Composite Part
Part Comprising a Coating on a Superalloy Metal Substrate, the Coating Including a Metal Underlayer
Method for Cleaning and Stripping a Turboshaft Engine Blade Using a Pulsed Laser
Sealing Device for a Turbomachine Turbine Nozzle
Exhaust Case for a Turbomachine with a Flexible Hub
Turbomachine Rotor with a Means for Axial Retention of the Blades
Compacting and Injection Mold for a Fiber Preform for Fabricating a Turbine Engine Guide Vane Made of Composite Material
Turbine Nozzle Guide Vane Assembly in a Turbomachine
Process for Injection Moulding a Composite Part
Turbojet Engine Cold Stream Flow Path Suspended from the Exhaust Case by Radial Crevice Mounts and Link Rods
Device for Mounting a Spark Plug in a Combustion Engine of a Gas Turbine Engine
Composite Turbomachine Blade with In-Built Root
Turbine Engine Rotor Including Blade Made of Composite Material and Having an Added Root
Method for Fabricating a Single-Piece Part for a Turbine Engine by Diffusion Bonding
Device for De-Icing a Turbomachine Separator
Annular Combustion Chamber for a Turbine Engine
Turbine Engine Impeller
Installation for Fabricating a Part by Selectively Melting Powder
Application:
14/118,623 →
Publication:
US 2014/0103015
Turbine Engine Fan Casing and an Assembly Formed by Such a Casing and Acoustic Panels
Application:
14/122,424 →
Publication:
US 2014/0212273
Pressure Maintaining Device for Creating Composite Components by Injecting Resin and Associated Method
Method and Device for Measuring a Part in a Turbine Engine
Gas Turbine Engine Comprising Three Rotary Bodies
Turbomachine with Bleed Valves Located at the Intermediate Case
Method of Reinforcing a Mechanical Part
Hall-Effect Thruster
Turbine Engine Comprising a Floating Bearing for Guiding a Shaft of the Turbine Engine
Blade, Particularly Variable-Pitch Blade, Propellor Comprising Such Blades and Corresponding Turbomachine
Dual-Flow Turbine Engine Having a Decoupling Device
Device for Classifying Strain Gauges
Turbomachine Element
Adaptive Machining Method for Smelted Blades
Device for Holding a Turbine Engine Blade for the Purposes of Machining
Ventilation of an Accessory Gear Box, and Turbojet Engine Comprising Such a Gear Box
Turbine Engine Part Forming a Compressor Stator or a Turbine Nozzle, and Method for Fabricating Same
Arrangement for Connecting a Duct to an Air-Distribution Casing
Unducted Propeller Gas Turbine Engine Attachment Structure
Accessory Relay Having an Extended Service Life
Turbine Engine Drive Shaft Device
Device and a Method for Measuring the Times of Passage of Blade Tips in a Turbine Engine
Application:
14/130,382 →
Publication:
US 2014/0126993
Labyrinth Seal for Gas Turbine Engine Turbine
Rotor Disk Including a Plurality of Hooks
Fixed Outside Ring of a Bearing with at Least One Drainage Orifice Passing Through a Guiding Edge of at Least One Rolling Element
System for Changing the Pitch of the Blades of a Propeller
Engine Cowl Incorporating an Equipment Ventilation Circuit
Device for Axial Locking of a Moving Part with Respect to a Reference Part
Fixed Turbine Engine Receiver Part Comprising an Assembly for Holding Ancillary Systems in Position Inside a Fixed Hollow Shaft
Method of Mixing Between a Primary Flow and a Secondary Flow in a Turbine Engine, Corresponding Device and Turbine Engine
Avionics Method and Device for Monitoring a Turbomachine at Startup
Lubrication System for a Turbopropeller
Method of Synchronising the Engines of an Aircraft
Oil Transfer System on Rotating Shaft
Blank Casting for Producing a Turbine Engine Rotor Blade and Process for Manufacturing the Rotor Blade from This Blank
Turbine Engine Blade
Anti-Rotation Device for a Large Size Nut
Method for Manufacturing a Turbine-Engine Fan Casing Having an Acoustic Coating
Aircraft Control and Monitoring System
A Device for Feeding Fluid to a Hydraulic Actuator for Controlling the Pitch of the Fan Blades of a Two-Propeller Turboprop
Turbine Engine Vane Plate Seal
Apparatus and Method for Carrying Out in a Controlled Atmosphere Material Fatigue Tests in a High Cycle Regime with a Controlled Strain Ratio
Method for Assembling a Titanium Shell with a Titanium Fire-Resistant Alloy Shell
Application:
14/234,300 →
Publication:
US 2014/0325823
Bladed Rotor Wheel for a Turbine Engine
Thrust Reverser Device for Compact Jet Pipe
Multi-Electrode Sensor for Determining the Gas Content in a Two-Phase Flow
A Device for Assisting in Cutting a Layer of Fiber Texture Wound on an Impregnation Mandrel of a Winding Machine
Method for Monitoring the Locking Means of an Electrical Thrust Reversal System for a Turbine Engine
Hydraulic System for Controlling the Orientation of Fan Blades
Method of Estimating the Temperature of the Fuel Leaving a Turbomachine Exchanger
Method of Casting Monocrystalline Metal Parts
Method of Making Protective Reinforcement for the Leading Edge of a Blade
Method of Determining the Appearance of Losses of Cohesion in a Transparent Ceramic Coating Layer Formed on a Substrate
Device for Shaping a Metal Sheet by Die Stamping
Method of Determining the Performance of at Least One Propeller of a Turbomachine in an Air Stream Under Gyration
Method of Fabricating a Part by Forging and Controlled Polishing
Turbo Engine Comprising a Damping Fluid Film for Damping a Guide Bearing of a Shaft of the Turbo Engine and Method of Adjusting the Thickness of Such a Damping Fluid Film
Ignition Device and Method for a Turbomachine Combustion Chamber
Assembly Formed by a Turbine Engine and a System for Attaching It to an Aircraft Structure
Turbine Engine Combustion Chamber
Bearing Test Bench
Installation of Calibration Gauge for Measuring Constraints
Turbomachine Vane Cooperating with a Vane Retention Disk
Turbine Engine Casing
System for Controlling the Pitch of the Propeller Blades of a Turbomachine, and a Turbomachine with a Propeller for an Aircraft with Such a System
Aircraft Turbofan Comprising an Intermediate Ring with Simplified Downstream Support
Propeller Blade Pivot
Interface Device Between Two Turbomachine Elements
Turbine Wheel in a Turbine Engine
Turbine Engine Wheel, in Particular for a Low Pressure Turbine
Monitoring the Fuel Supply Cutoff Valve for an Engine
Process, System and Computer Program Product for Asset Maintenance
Application:
14/299,487 →
Publication:
US 2014/0372289
Assembly for a Turbine Engine
Method of Producing Suspension for a Structure in a Turbojet Engine Using a Hyperstatic Trellis with Pre-Stressed Link Elements
Device with Multiple Reduction Gear Transmission Between a Drive Shaft and a Pair of Propellers Coaxial with This Shaft
Insert with an External Surface Which Is Part of at Least One Aerodynamic Profile of a Turbomachine Test Blade
Tail Cone for a Microjet Rotary Turbine Engine
Exhaust Centerbody for a Turbine Engine
Biconical Exhaust Cone for a Civil Aviation Jet Engine
Application:
14/340,047 →
Publication:
US 2015/0028129
Control Device for the Pitch of Blades, and Propeller
Device for Guiding Variable Pitch Diffuser Vanes of a Turbine Engine
Method and Device for Manufacturing a Cylindrical Part from Composite Material
Oil and Fuel Circuits in a Turbine Engine
System for Monitoring a Measurement Chain of a Turbojet Engine
Electric Propulsion System with Stationary Plasma Thrusters
Annular Combustion Chamber for a Turbine Engine
Method of Determining Whether to Replace a High Pressure Pump in a Hydraulic Regulation System of a Turbomachine
Primary Cowl of a Turbofan Comprising a Rotating Ring Having Micro-Jets
Method for Welding and for Hard Surface Deposition of Metal Parts Made of Aluminium by a Mig Method with Pulsed Current and Filler Wire
Blade for a Fan of a Turbomachine, Notably of the Unducted Fan Type, Corresponding Fan and Corresponding Turbomachine
One-Block Bladed Disk Provided with Blades with Adapted Foot Profile
An Annular Combustion Chamber in a Turbine Engine
Turbomachine Centre Blade Comprising a Curved Portion
Device for Fabricating a Composite Material Part
Turbo Engine with Propeller(S) for an Aircraft with a System for Changing the Pitch of the Propeller
High Moisturizing Cleansing Composition Containing a Lamellar Phase
Device for Holding a Fiber Texture on an Impregnation Mandrel of a Winding Machine
Impregnation Mandrel with Vacuum Liner for Making a Gas Turbine Casing Made of Composite Material
Impregnation Clamping Mandrel for Making Gas Turbine Casings Made of Composite Material
Annular Wall of a Combustion Chamber with Improved Cooling at the Level of Primary and/or Dilution Holes
Method of Fabricating a Part Made Out of TA6ZR4DE Titanium Alloy
Application:
14/353,404 →
Publication:
US 2014/0286783
Method and a Device for Estimating a Porosity Ratio of a Sample of Material from at Least One Gray-Scale Coded Image
Aircraft Turbomachine Combustion Chamber Module and Method for Designing Same
Method for Producing a Metal Part for an Aircraft Turbo-Engine
Method of Fabricating a Turbine or Compressor Guide Vane Sector Made of Composite Material for a Turbine Engine, and a Turbine or a Compressor Incorporating Such Guide Vane Sectors
Installation for Fabricating Parts by Selective Melting of Powder
Attachment Pylon for a Turbine Engine
Pressure-Maintenance Device for Producing Composite Parts by Resin Injection and Associated Method
Rotor Wheel for a Turbine Engine
System and Method for Dynamically Locating a Fault Observed on a Component
Method for Reshaping a Turbomachine Blade That Has at Least One Zone That Has Become Deformed Using Peening
Design for a Part Made from 3D Woven Composite Material
Gas Turbine Blade with Tip Sections Offset Towards the Pressure Side and with Cooling Channels
Steerable Hall Effect Thruster Having Plural Independently Controllable Propellant Injectors and a Frustoconical Exhaust Outlet
Mechanical System for a Turbine Engine, Turbine Engine, and Method for Attaching a Mechanical System Within a Turbine Engine
Turbine Engine Blade, in Particular for a One-Piece Bladed Disk
Method of Fabricating a Composite Material Turbine Engine Vane with Incorporated Platforms
Unlockable Device for Axially Arresting a Sealing Ring with Which an Aircraft Turbomachine Module Rotor Wheel Makes Contact
Hollow-Blade Turbine Vane Made from Composite Material, Turbine or Compressor Including a Nozzle or Guide Vane Assembly Formed by Such Blades, and Turbomachine Comprising Same
Method for Creating a Connecting Element Positioned Between Two Components of a Structure, Connecting Element and Bypass Turbojet Engine Comprising Such a Connecting Element
Application:
14/362,267 →
Publication:
US 2014/0311161
System for Sealing an Oil Chamber from an Adjoining Exterior Volume and Turbo-Machine Provided with Such a Sealing System
Convergent-Divergent Nozzle for a Turbine Engine
Fluid Discharge Vibration Damping Strips for Acoustic Protection of Aircraft Turbomachine Fan Casing
Turbomachine Compressor Guide Vanes Assembly
Fibrous Reinforcement Structure for Composite Material Part Having a Reduced Thickness Portion
Fibrous Structure Having Variable Numbering Yarns
Jacquard Loom Having Optimized Warp Yarn Density
Method for Measuring Elastic Properties Using Ultrasound
Fiber Preform of Pi-Shaped Section, in Particular for a Fan Platform Made of Composite Material
3D Woven Fiber Structure, a Fiber Preform Obtained from Such a Fiber Structure, and a Composite Material Part Including Such a Preform
Fiber Structure Woven as a Single Piece by 3D Weaving and Application to the Manufacturing of Composite Material Part
Method of Fabricating a Turbine Engine Shaft
Method and Device for Estimating a Thickness of a Ceramic Thermal Barrier Coating
Method of Manufacturing a Ceramic Core for Mobile Blade, Ceramic Core and Mobile Blade
Device for Surfacing a Metal Alloy Part
Tool for Machining a Wall of a Workpiece, in Particular Made from a Composite Material
System for Acquiring a Vibratory Signal of a Rotary Motor
Fiber Preform for a Turbine Engine Blade Made of Composite Material and Having an Integrated Platform, and a Method of Making It
Composite Material Reinforcing Part of Pi-Shaped Section, in Particular a Platform for a Turbine Engine Fan, and Its Method of Fabrication
Sealing Device Between Two Axisymmetric Coaxial Parts
Turbomachine Rotor Blade
Angular Diffuser Sector for a Turbine Engine Compressor, with a Vibration Damper Wedge
Optimisation of the Bearing Points of the Stilts of Vanes in a Method for Machining Said Vanes
Application:
14/373,817 →
Publication:
US 2014/0369844
Method for Repairing Wear Marks on a Rotor Supporting the Fan of a Bypass Engine
Method for Producing a Propeller Blade from a Composite Material
Turbojet Fan Blade
Method and System for Attaching a Piece of Equipment to a Structure Made from Composite Material
Hall Effect Thruster Having an Annular Chamber With Movable Inner/Outer Wall
Device for Injecting Air and Fuel into a Combustion Chamber of a Turbine Engine
Linear Gasket for an Inter-Blade Platform
Turbine Engine Fuel Injector with Permanent Leakage Flow
Turbine Engine Fuel Injector with Leakage Flow Controlled by Position of Metering Valve
Device for Recovering Lubricating Oil from an Epicyclic Reduction Gear
Method of Producing Tooling for Resin Transfer Molding
A Method of Making Safe the Operation of a Turbomachine
Foundry Core Assembly for Manufacturing a Turbomachine Blade, Associated Method of Manufacturing a Blade and Associated Blade
Method for Holding an Adapter Piece on a Tubular Housing of a Turbo Engine, and Corresponding Adapter Piece and Holding System
Device for Detecting Anomalies in an Aircraft Turbine Engine by Acoustic Analysis
Turbomachine Blade Comprising an Insert Protecting the Blade Tip
Vortex Generators Placed in the Interblade Channel of a Compressor Rectifier
Method of Impregnating Ceramic Cores for the Manufacture of Turbomachine Blades
Application:
14/384,556 →
Publication:
US 2015/0044382
Casing for Turbomachine Blisk and Turbomachine Equipped with Said Casing
Turbine Engine, Such as a Turbojet or a Turboprop Engine
Method for Disassembling a Reinforcement from a Part
Detecting and Tracking Damage to an Aeroengine Fan or an Impact of a Foreign Object Thereagainst
Ignition Unit for Turbojet Engine
Electrically Controlled Actuating Device Incorporating a Thermostatic Function, and Valve
Stator Vane Formed by a Set of Vane Parts
Variable Pitch Rectifier for a Turbomachine Compressor Comprising Two Inner Rings
Compressor Casing Comprising Cavities with Optimised Setting
Turbomachine Rotor Blade
Device for Sealing Between the Coaxial Shafts of a Turbomachine
Compressor Casing Comprising Cavities Having an Optimised Upstream Shape
Method and Tooling for Assembling a Guide Vane Stage
Correction of a Temperature Measurement of a Thermometric Resistance-Type Temperature Probe
Coupling of Shafts Using Variable-Profile Splines
Turbomachine Combustion Chamber Shell Ring
Turbine Stage for a Turbine Engine
Method for Creating a Metal Reinforcement with Insert for Protecting a Leading Edge Made of Composite
Method of Fabricating a Bath of Electrolyte for Plating a Platinum-Based Metallic Underlayer on a Metallic Substrate
Method for Machining the Trailing Edge of a Turbine Engine Blade
Turbomachine Comprising a Monitoring System Comprising a Module for Engaging a Protection Function of the Turbomachine and Monitoring Method
Turbine Engine Incorporating Thermoelectric Generators
Tool for Loosening a Connecting Nut of a Rotor of a Module for a Gas-Turbine Engine
Method for Removing a Turbofan Engine Using a Heating Device
Fiber Blank Woven as a Single Piece by Three-Dimensional Weaving to Make a Closed Box-Structure Platform Out of Composite Material for a Turbine Engine Fan
Tool and Method for Frontal Unscrewing of a Link Nut in a Twin-Spool Turbine
Metal Structural Reinforcement for a Composite Turbine Engine Blade
Method for Improved Assembly of an Actuator for an Air Bleed Valve of a Turbine Engine
Method for Hard-Surfacing Metal Parts for Aircraft Turbofans, and Local Protection Tool for Implementing the Method
Information Processor System for Monitoring a Complex System
Tool for Manufacturing a Foundry Core for a Turbine Engine Blade
Device for Handling Wax Spider-Like Sprues
Method for Monitoring a Degradation of an on-Board Device of an Aircraft with Automatic Determination of a Decision Threshold
Turbomachine Distributor and Production Method
Application:
14/401,334 →
Publication:
US 2015/0125289
Turbine Engine Comprising an Upstream Attachment Means for a Deoiling Pipe
Method of Making a Metal Reinforcing Member for a Blade of a Turbine Engine
Airplane Turbojet Fan Blade of Cambered Profile in Its Root Sections
Method for Compacting Anodic Paints, Including the Collision of Sandblasting Jets
Gas Turbine Engine Comprising an Exhaust Cone Attached to the Exhaust Casing
Information Processing System and Method for Monitoring a Complex System
Fluid Circuit in a Turbine Engine
Method and Device for Drilling a Workpiece with Laser Pulses
Fan Having a Variable Setting by Means of Differential Rotation of the Fan Disks
Bearing with Lubrication Means and System for Changing the Pitch of the Blades of a Turboprop Propeller of an Aircraft Equipped with Said Bearing
Turbine Engine Stator Wall Covered in an Abradable Coating
Counter Plate and Turbo Machine Comprising a Counter Plate
Calibration Head for the Drilling of Shafts
Process for Complete Cladding of Metal Parts of Aircraft Turbojets, and Complete Protection Tool for Implementing the Process
Forecasting Maintenance Operations to Be Applied to an Engine
Journal for a Turbine Engine Comprising a Ring for Recovering a Flow of Lubricating Oil with a Plurality of Lubricating Oil Discharge Ports
Monitoring a Linear Variable Differential Transformer Sensor
Method and a Device for Adjusting a Setpoint Value of a Parameter That Influences Thrust from a Gas Turbine Engine
Method and Device for Adjusting a Threshold Value of a Fuel Flow Rate
Gas Turbine Engine Comprising a Composite Component and a Metal Component Which Are Connected by a Flexible Fixing Device
Device for Ventilating and Supplying Electrical Power to an Aircraft Engine Computer
Gasket Device for the Bearing of a Turbomachine, Comprising Two Elastic Seals
Application:
14/412,336 →
Publication:
US 2015/0184531
Method and Tool for the Vapour Phase Deposition of a Metal Coating Onto Parts Made of Superalloys
Method of Fastening Structural Metal Reinforcement on a Portion of a Gas Turbine Blade Made of Composite Material, and an Injection Mold for Performing Such a Method
Device for Spraying a Dye Penetration Inspection Liquid into a Workpiece
Device for Simulating the Ingestion of Chunks of Ice by an Engine
Turbomachine Guide Vanes with Improved Vane Profile
Application:
14/413,042 →
Publication:
US 2015/0226074
Method for Detecting Deterioration in a Turbomachine by Monitoring the Performance of Said Turbomachine
Method of Characterizing an Object Including, at Least Locally, a Plane of Symmetry
Part to Modify the Profile of an Aerodynamic Jet
Turbomachine Vane Having an Airfoil Designed to Provide Improved Aerodynamic and Mechanical Properties
Device for the Transfer of Heat Between a Lubrication Pipe and a Turbomachine Blade Pitch Actuator Control Hydraulic Pipe
Application:
14/414,343 →
Publication:
US 2015/0219014
Method and System for Cutting a Preform Intended for the Production of a Turbomachine Part
Method for Manufacturing a Turbomachine Casing from a Composite Material and Associated Casing
Cooling of an Oil Circuit of a Turbomachine
Corrosion-Resistant Abradable Covering
Engine-Control Computer and Method for Detecting Failures of Such a Computer
Constant-Volume Combustion (Cvc) Chamber for an Aircraft Turbine Engine Including an Intake/Exhaust Valve Having a Spherical Plug
Method for the Non-Destructive Testing of a Blade Preform
Abradable Coating Made of a Material Having a Low Surface Roughness
Turbomachine Comprising a Plurality of Fixed Radial Blades Mounted Upstream of the Fan
Power Supply Circuit
Moving Turbine Blade
Method of Characterizing an Article Made of Composite Material
Method of Measuring the Temperature Reached by a Part, in Particular a Turbine Engine Part
Tooling for Removing Sand from a Turbine Engine
Turbine Rotor for a Turbomachine
Drive Gearbox on a Turbomachine, Consisting of a Drive Train with Gear Lines Extending into Non-Parallel Planes
Method for Producing Preforms
Air Supply Device for Aircraft Engine Turbines
Fan Rotor, in Particular for a Turbine Engine
Method of Determining the Non-Propagation Threshold of Fatigue Cracks at High Frequency
Device for Sealing an Opening of an Enclosure Wall for Access to a Rotary Shaft
Application:
14/426,125 →
Publication:
US 2015/0233463
Turbine Engine Comprising a Means for Measuring the Speed and Torque of a Shaft of the Turbine Engine and Method for Monitoring Said Shaft
Method for Mounting an Acoustic Panel in a Housing of a Turbomachine and Turbomachine Comprising an Acoustic Panel
Pylon for Mounting an Engine on the Structure of an Aircraft
Cooled Vane of a High-Pressure Turbine
Casting Pattern
Turbomachine Distributor Comprising a Thermal Protection Sheet with a Radial Stop, and Associated Thermal Protection Sheet
Machine for Winding a Fibrous Material Enabling Alignment and Off-Centering Control by Image Analysis
Shell Mould Having a Heat Shield
System for Holding Blades and Assembly Method
Turbine Engine Casing and Rotor Wheel
Hydraulic and Electrical Interface Ring for a Turbine Engine
Self-Clamping Fastener for Cmc Turbine Blade
Method of Identifying and/or Tracking Deformation of a Turbine Engine Part
Multi-Sensor Measuring Method and System
Method for Monitoring a Thrust Fault of an Aircraft Turbofan
Propeller Comprising a Moveable Dynamic Scoop
A Method of Surface Marking a Mechanical Part with a Predefined Graphical Representation Visible to the Naked Eye
Method for Manufacturing at Least One Metal Turbine Engine Part
Jet Pump for Depressurizing Lubrication Chambers of a Turbomachine, Having Independent Double Injectors
Device and Method for Controlling the Pitch of Blades
Part Consisting of a Ceramic Material, Comprising a Base and a Wall
Method for Differentiating Control Failures in a System for Controlling an Actuator, in Particular of a Stator of a Gas-Turbine Engine
System for Monitoring a Set of Components of a Device
Aircraft Propelled by a Turbojet Engine with Contrarotating Fans
System for Attaching Electrical Equipment to a Metallic Support
Propellant Gas Supply for an Ionic Propulsion Unit
Exhaust Housing Hub for a Turbomachine
Turbomachine Casing
Method for Resurfacing at Least One Arm of an Intermediate Casing of a Turbomachine
Application:
14/440,427 →
Publication:
US 2015/0251281
Device for Controlling Blade Angle, and Propeller
Method for Monitoring an Ignition Sequence of a Turbomachine Engine
Method and System for Determining the Flow Rate of Air Collected from an Aircraft Engine
Air Exhaust Tube Holder in a Turbomachine
Air Exhaust Tube Holder in a Turbomachine
Air Conditioning Method and System for Aircraft
Monobloc Preform and Blade for Turbo Machine
Monobloc Blade Preform and Module for a Turbo Machine Intermediate Casing
Electrical Installation Having a Cooled Fuel Cell Comprising an Absorption Heat Engine
Turbomachine Comprising a Device for the Cooling of a Pylon
Turbine Casing Made of Two Materials
Turbine Engine Having an Element for Deflecting Foreign Objects
Electrode for Forming a Cooling Channel in a Wall
Blisk with Low Stresses at Blade Root, Preferably for an Aircraft Turbine Engine Fan
Process for Smoothing the Surface of a Part Made of Cmc Material
Tank Having an Inclined Partition Provided at Its Ends with Through-Holes for Continuous Supply of a Supply Liquid to a Turbine Engine
Case Structure Interposed Between the Engine and the Nacelle with Jointed Ferrule Segments
Assembly Forming a Seal for a Turbomachine Including a Brush Seal and at Least One Lip
Application:
14/474,463 →
Publication:
US 2015/0308280
Method for Monitoring a Degradation in an on-Board Device of an Aircraft with Automatic Determination of a Decision Threshold
Angular Stator Sector for a Turbomachine Compressor Comprising a Brush Seal
Method and a Device for Normalizing Values of Operating Parameters of an Aeroengine
Arrangement for a Tank Between a Nacelle Cowling and a Turbomachine
Tightening and Oil Discharging Nut, and a Turbine Engine
Device for Suspending a Casing, a Turbine Engine and a Propulsion Assembly
Exhaust Casing Comprising a Fluid Discharge Device and Turbine Engine
Device for Connecting a Fixed Portion of a Turbine Engine and a Distributor Foot of a Turbine Engine Turbine
Device for Connecting a Fixed Portion of a Turbine Engine and a Distributor Foot of a Turbine Engine Turbine
Application:
14/503,743 →
Publication:
US 2015/0315931
Power Transmission System for a Turbine Engine
Non-Regression Method of a Tool for Designing a Monitoring System of an Aircraft Engine
Fuel Injector for a Turbine Engine
Labyrinth Seal and Rotating Machine Comprising Such a Seal
Turbine Engine Vane with Asymmetrical Profile
Instrumented Airfoil
Composite Vane for a Turbine Engine
Application:
14/526,754 →
Publication:
US 2016/0153295
Metallisation of an Electrically Insulating Housing of an Aeronautic Engine
Metallisation of a Housing of an Aeronautic Engine Made of Electrically Insulating Material
Turbine Engine Comprising Means for Supporting at Least One Item of Equipment
Device for Supplying Oil Under Pressure to a Linear Actuator of a Turbine Engine
Bearing Cage with a Peripheral Vibration Damping Ring
Bearing Support Having a Geometry for Easier Evacuation of Casting Cores
Method to Test Equipment with Variable Geometries of an Aircraft Engine
Valve for Fuel Circuit of an Aircraft Engine
Annular Wall for Turbomachine Combustion Chamber Comprising Cooling Orifices Conducive to Counter-Rotation
Application:
14/564,588 →
Publication:
US 2015/0167977
Multipurpose Electrical Discharge Machining Tool for a Ring Sector
Variable Pitch Guide Vane Made of Composite Materials
Fluid Intake System
Detection Device for Initiating Failures of a Mechanical System
Casing for a Propulsion Unit
Suspension for a Turbine Engine
Heat Exchanger for a Turbo Engine
Blade Comprising a Support, Provided with a Portion with a Depression
Application:
14/579,426 →
Publication:
US 2015/0176415
Turbomachine Assembly Comprising Two Bodies and Means for Guiding a Fluid Flowing from One Body to the Other
Methodology and a System to Create 3D Specifications for the Assembly of Parts of a Complex System
Application:
14/590,587 →
Publication:
US 2016/0196036
Blade with 3D Platform Comprising an Inter-Blade Bulb
Method of Preheating a Set of Shell Molds for Lost-Wax Casting
Heat Exchanger of a Turbomachine
Part Comprising a Structure and a Shape Memory Alloy Element
Semiconductor Igniter Plug for an Aircraft Turbomachine, Comprising Scoops for Discharging Possible Fuel Residues
Turbine Engine Having a Pair of Propellers for an Aircraft
Instrumented Vane
Injection Mold Core for Making a Part Out of Composite Material, the Part Having a Closed Box
Rotating Inlet Cowl for a Turbine Engine, Comprising an Eccentric Forward End
Turbomachine Comprising a Plurality of Fixed Radial Blades Mounted Upstream of the Fan
Turbomachine Comprising a Plurality of Fixed Radial Blades Mounted Upstream of the Fan
Turbine Engine with a Combustion Chamber Outer Flange of Sandwich Type
Assembly Forming a Gasket for a Turbomachine, Comprising a Brush Seal
Application:
14/646,872 →
Publication:
US 2015/0300191
A Method for the Additive Manufacturing of a Part by Selective Melting or Selective Sintering of Optimized-Compactness Powder Beds Using a High Energy Beam
Method for Friction Welding a Blade Onto a Turbine Engine Rotor Disc; Corresponding Integral Blade Disc
Control Device for an Engine
Turbine Engine Cowl Capable of Covering a Fan Cone
Method for Manufacturing a Part by Melting Powder, the Powder Particles Reaching the Bath in a Cold State
Method and Device for Acoustically Detecting a Malfunction of a Motor Having an Active Noise Control
Removable Acoustic Panels for Turbojet Engine Casing
Method for Manufacturing a Turbine Engine Blade Root of a Composite Material and Blade Root Obtained by Such a Method
System for Measuring an Oil Retention Volume in a Lubricating System
Propeller Blade for a Turbomachine
A Method of Balancing a Turbine Engine Rotor, and a Rotor Balanced by Such a Method
Application:
14/650,043 →
Publication:
US 2015/0315914
Optimising the Availability of a Thrust Reverser
Intermediate Casing Extension of Improved Design
Method for Characterising a Part Made of a Composite Material
Turbomachine Fuel Circuit
Double Tube Connecting Device
Turbojet with a Discharge Duct
Method for Reducing the Diameter of an Opening
Application:
14/664,415 →
Publication:
US 2015/0258597
Balancing Device and Method
Device for Fixing Reactor Modules to a Test Bench
Turbomachine Part Comprising a Flange with a Drainage Device
Bench Test, for the Characterization of a Flow of a Two-Phase Fluid
Device for Locking a Nut
System and Method for Maintaining an Aircraft Engine
Attachment of a Discharge Conduit of a Turbine Engine
Method and Device for Ultrasound Inspection of Welds, Particularly Welds of Blades on the Disk of a Bladed Disk
Rotating Assembly for a Turbomachine
Annular Combustion Chamber
Method for Detecting a Fluid Leak in a Turbomachine and System for Distributing a Fluid
Balanced Rotor Disc, and Balancing Method
Turbine Engine Wall Having at Least Some Cooling Orifices That Are Plugged
Variable geometries fluid supply circuit and Fuel injection system supply circuit
Application:
14/717,702 →
Publication:
US 2015/0337734
Propulsion Unit with a Pair of Propellers for an Aircraft
Device and Method for Localizing a Position on a Part
Holding Device of a Cooling Tube for a Turbojet Casing
Instrumented flow passage of a turbine engine
Aircraft Turboprop Engine Comprising Two Coaxial Propellers
Turbomachine Vane Including an Antivortex Fin
Two Stage Pump, Particularly Provided as Main Pump for Supplying an Aircraft Engine with Fuel
Injection System for a Turbine Engine Combustion Chamber Configured for Direct Injection of Two Coaxial Fuel Flows
Method for Determining a Duration of Movement for a Starter Air Valve of a Turbine Engine
Device for Measuring the Internal Profile of a Hollow Shaft
Method for Manufacturing a Component Using the Lost-Wax Casting Method with Directed Cooling
Device for Sealing Between the Coaxial Shafts of a Turbomachine
Rotating Machine Comprising a Damping Collar
Balancing Screw, Device and Method for a Rotating Part of a Turbine Engine
An Acoustically Optimized Air Inlet
Assembly of a Balance Weight with a Rotor Element
Suspension Structure with Variable Geometry of a Turboprop Engine on a Structural Element of an Aircraft
Fixed Diffuser Vanes Assembly for Guiding Flow Through a Turbomachine, Comprising an Internal Platform with Inbuilt Reinforcements, and Associated Turbomachine and Production Method
Auxiliary Device for Welding Spindle Disks, Having a Damping Belt, and Friction Welding Method
Device for Securing and Retaining at Least One Electrical Harness in a Turbomachine
Turbomachine Rotor Blade
Mold Comprising Shells and at Least One Slide
Flow Distribution Blading Comprising an Improved Sealing Plate
Anti-Rotation Nozzle Sector and Method for Manufacturing Such a Sector
Turbojet Engine Suspension Using a Double Rear Support
Tool for Fitting an Inner Bearing Race Carrying a Bearing Cage and Screws for Retaining in a Turbomachine
Cooling Device for the Casing of an Aircraft Jet Engine Comprising a Supporting Device
Method and Device for Regulating the Cooling of Oil in a Turbomachine
Method for Producing a Rotor Vane for a Turbomachine
Variable-Pitch Vane
Compact Dosing Device for an Injector with Two Fuel Circuits for an Aircraft Turbomachine
Turbine Engine, Such as an Airplane Turbofan or Turboprop Engine
Application:
14/775,141 →
Publication:
US 2016/0032834
V-Shaped Gearbox for Driving Turbomachine Equipment
Fan for a Multi-Flow Turboshaft Engine, and Turboshaft Engine Equipped with Such a Fan
Application:
14/776,300 →
Publication:
US 2016/0032734
Blade and Blade Dihedral Angle
Injection System for a Combustion Chamber of a Turbine Engine, Comprising an Annular Wall Having a Convergent Inner Cross-Section
Ball Joint Device for Suspending a Turbine Engine on a Pylon or Suspending Equipment on the Body of the Turbine Engine
Disengageable Axial Thrust Bearing with Internal Preload
Bearing with Double Pre-Loading
System for Detecting Defects on an Object
Fan Disk for a Jet Engine and Jet Engine
Monocrystalline Casting Mold
Device for Deicing a Separator Nose of an Aviation Turbine Engine
Method for Manufacturing an Asymmetric Component Using Additive Manufacturing
Shot Peening Deformation Process for Assembling Two Parts of a Turbomachine
Application:
14/784,194 →
Publication:
US 2016/0032741
Method for Modelling a Part, in Particular a Blading
Aircraft Load Shedding System Including Supplementary Power Sources for Assuring DC and Device for Cutting Off Power to the Alternators of a Turbine Engine During Acceleration
Method for Analysing a Fracture Face of a Part of a Turbine Engine
A Method and a Device for Generating a Command for the Flow Rate of Fuel That Is to Be Injected into a Combustion Chamber of a Turbine Engine
A Structure for Suspending a Turboprop Having Two Unducted Propellers on a Structural Element of an Airplane
A Method of Measuring the Thickness of a Fiber Texture Wound Onto an Impregnation Mandrel, and a Winder Machine Implementing Such a Method
Emc Test Bench Comprising an Item of Equipment Under Test Which Is Intended to Be Loaded on Board an Aircraft
Machine for Weaving or Winding a Fiber Texture and Enabling Anomalies to Be Inspected by Image Analysis
Undulating Stator for Reducing the Noise Produced by Interaction with a Rotor
Intermediate Casing for a Turbofan Engine
Device for Assisted Maintenance of an Aircraft Engine by Recognition of a Remote Movement
Application:
14/804,396 →
Publication:
US 2016/0026256
Method of Monitoring Short Circuits in Torque Motors
Device for the Nondestructive Test of a Part
Fuel Meter Protected from Icing
System for Reproducing a Dry Friction Torque Applied to an Actuator of a Valve Located in a Hydraulic Line of an Engine of a Spacecraft Including an Electrical Actuator Controlling Orthogonal Forces of Plates on a Disc to Apply Resistive Torque to a Shaft of the Actuator
Method of Designing a Common Preform for Providing Preforms for Turbine Engine Outlet Guide Vanes of Different Geometrical Profiles and Made Out of Composite Material
Turbine Wheel for a Turbine Engine
Method for Determining at Least One Faulty Piece of Equipment of an Aircraft, and Corresponding System
Monitoring of an Aircraft Propulsion System
Turbine Engine Comprising a Device for Braking the Fan Rotor
System for Controlling Variable-Pitch Vanes for a Turbine Engine
Method for Immobilising a Preform in a Mould
Tooling for Fastening Metal Reinforcement on the Leading Edge of a Turbine Engine Blade, and a Method Using Such Tooling
Seal Assembly for a Turbine Engine Comprising Means for Lubricating a Brush Seal
Method and System for the Vibration Analysis of an Engine
Apparatus and Method for Optimizing a Test Bed That Is Utilized for Testing Low Cycle and High-Cycle Fatigue Including Modifying a Support
Test Bench Combining High-Frequency Tribological Stress and Oligocyclic Fatigue, on a Blade Disk of Turboshaft Engine of an Aircraft Including a Test Piece Having a Portion with a Shape of a Blade Root of a Rotor and Is Engaged in a Groove Shape Complementary to Another Test Piece
Oligocyclic Fatigue or Oligocyclic and Polycyclic Fatigue Test Rig
Aircraft Turbopropeller
Turbomachine Auxiliary Lead-Through Device
Hollow Vane, and Associated Production Method
Rotor Disk Blade with Friction-Held Root, Rotor Disk, Turbomachine and Associated Assembly Method
Improved Method for Inspection by the Transmission of Ultrasounds
Turbomachine Casing Comprising an Endoscopy Port
Turbine Engine Blade Preform
Accessory Drive Case for a Turboprop
Device for Fixing Two Parts Together
Methods of Creating a Database and of Formulating a Map of Operating States of Aircraft and a Method of Monitoring the Operation of an Associated Aircraft
Trunnion for High-Pressure Turbine, and Turbojet Engine Including Such a Trunnion
Process, System and Computer Program Product for Asset Maintenance
Application:
14/897,950 →
Publication:
US 2016/0125518
Method for Producing Cavities for a Turbomachine Disk
Method and System for Resetting a Digital Model
Turbomachine Accessory Gearbox Equipped with a Centrifugal Pump
Application:
14/898,906 →
Publication:
US 2016/0305331
Ventilation of a Turbomachine Nacelle
An Air Propeller Blade Pivot in the Shape of a Spherical Cap
Improved Intermediate Casing for Turbomachine and Accessory Gearbox Drive Assembly
Remote Connection System for an Aircraft
Bearing Nut for Measuring the Rotational Speed of a Shaft Connected to a Turbomachine and Associated Measuring Device
Augmented Reality Method and System for Monitoring
Application:
14/902,180 →
Publication:
US 2016/0371887
Process for Preparing a Substrate for Thermal Spraying of a Metal Coating
Process for Additive Manufacturing of Parts by Melting or Sintering Particles of Powder(S) Using a High-Energy Beam with Powders Adapted to the Targeted Process/Material Pair
Device for Inspecting a Surface of an Electrically Conductive Part
Coating of a Turbine Engine Part by Overinjection
Turbine Engine Casing Having a Cut-Out Flange
Composite Propeller Blade for an Aircraft
Method for modeling a non-axisymmetric surface
Device for Cooling Oil for a Turbine Engine
Nozzle of a Turbomachine Provided with Chevrons with a Non-Axisymmetric Inner Face
Method for Assembling Turbomachine Parts and Assembly Used During Such a Method
Device for Protecting Against Oil Leaks Towards the Rotors of a Turbomachine Turbine
Cover of a Turbomachine Centrifugal Compressor Capable of Being Rigidly Connected via the Downstream Side Near to the Upstream Edge of Same, and Turbomachine Comprising This Cover
Dismantling Device for Blades and Corresponding Dismantling Method
Method for Producing a Metal Undercoat Made from Platinum on a Metal Substrate
Application:
14/905,173 →
Publication:
US 2016/0153106
Protection Cover for a Spray Nozzle During a Hardfacing Process
Method of Estimation on a Curve of a Relevant Point for the Detection of an Anomaly of a Motor and Data Processing System for the Implementation Thereof
Hub of an Intermediate Casing for an Aircraft Turbojet Engine Comprising Doors with Contoured Geometry
Turbine Engine Casing and Manufacturing Method
Epicyclic Reduction Gear with Fluid Transfer Pipes, and Propeller Turbomachine for an Aircraft with Such a Reduction Gear
Ventilation of a Piece of Electronic Equipment of a Turbomachine
Method for Modeling a Non-Streamlined Propeller Blade
Method for Monitoring a Valve of an Aircraft Engine
Fuel Circuit of an Aircraft Engine with a Fuel Recirculating Valve Controlled by a Pressure Differential of a Low-Pressure Pump of the Fuel System
Turbine Engine Rotor Blade
Method and Module for Filtering a Raw Setpoint
Turbomachine Impellor Rotor with Device for Feathering the Blades of the Impellor
Improvement for the Locking of Blade-Supporting Components
Turbomachine Provided with an Assembly for Controlling the Pitch Variation of a Propeller
Turbine Engine Guide Vane
Method and System for Injecting Fuel into an Engine Combustion Chamber
Method for the High-Temperature Shaping of a Metal Blade Reinforcement
Casing Structure Interposed Between the Engine and the Nacelle Having a Mounting Plate with Bolts
Afterbody for a Mixed-Flow Turbojet Engine Comprising a Lobed Mixer and Chevrons with a Non-Axisymmetric Inner Surface
Application:
14/914,235 →
Publication:
US 2016/0215727
Rotating Assembly Comprising a Transmission Member and an Oil Distribution System
Isostatic Suspension of a Turbojet by Rear Double Support
Method of Fabricating a Reinforcing Edge for a Blade and Reinforcing Edge Obtained by the Method
A Casing Structure with Connection Tabs
Casing Structure Interposed Between the Engine and the Nacelle Having Pivoting Shroud Sectors
Multipoint Fuel Injection System for a Turbomachine and Associated Regulation Method
Driving Assistance Device, Method and Computer Program That Can Be Stored in a Memory of a Mobile Terminal in Order to Operate the Device
Rotor Blade with Reduced Acoustic Response
Turbomachine Comprising an Electric Current Generator Allowing Oil Injection from the Inside of a Rotor Shaft
Circuit for De-Icing an Air Inlet Lip of an Aircraft Propulsion Assembly
Application:
14/923,214 →
Publication:
US 2016/0114898
Air Intake Sleeve for an Aircraft Turboprop Engine
Application:
14/924,437 →
Publication:
US 2016/0123228
Method and a Circuit for Ventilating Equipment of a Turbojet by Thermoelectricity
Application:
14/926,628 →
Publication:
US 2016/0123185
Propeller Ring Made of Composite Material for a Turbomachine
Turbine Wheel for a Turbine Engine
Turbine Wheel for a Turbine Engine
Fairing for a Mixer of a Nozzle of a Dual-Flow Turbomachine
Single-Piece Blisk for Turbomachine Fan Comprising an Upstream and/or Downstream Recess Making Its Blades More Flexible
A Coating for Protection Against Oxidation and Against Hot Corrosion on a Superalloy Substrate
Casing Support Structure
System for Painting a Splayed End of a Hollow Shaft on a Rotary Paint Bench
Turbine Engine Rotor Shaft Comprising an Improved Heat Exchange Surface
Reduction of Turbofan Noise
Turbomachine Blade, Comprising Intersecting Partitions for Circulation of Air in the Direction of the Trailing Edge
Annular Deflection Wall for a Turbomachine Combustion Chamber Injection System Providing a Wide Fuel Atomization Zone
Application:
14/950,518 →
Publication:
US 2016/0153662
Device and Method for Regulating a Motor Using a Thrust Measurement
Method for Reducing the Noise Level of a Turbomachine Fan
Platform of Small Hub-Tip Ratio
Impeller Having Spoilers for a Turbine Engine Turbine
Impeller Having a Radial Seal for a Turbine Engine Turbine
Mechanism for Driving Blade Orientation Adjusting Members
Air Circulation Device for Turbomachine
Turbomachine Rotor with Optimised Bearing Surfaces
Method for Manufacturing a Propeller Blade
Method for Monitoring the Energy Density of a Laser Beam by Image Analysis and Corresponding Device
Device for Supplying Hydraulic Fluid to a Ram and Mechanism for Controlling the Pitch of the Blades of a Turbine Engine Propeller Comprising the Ram
Hydraulic Connection Device and Fluid Transfer System Using Said Device
Turbine Engine Nozzle Having Confluent Streams and Including a Core Cowl with Overlapping Flaps
Combustion Chamber for a Turbine Engine with Homogeneous Air Intake Through Fuel Injection System
Jet Pump for Turbomachine Lubrication Chamber Depressurization Circuit
Turbomachine Combustion Chamber Provided with Air Deflection Means for Reducing the Wake Created by an Ignition Plug
Fuel Injector for a Turbine Engine
Compacting Assembly and Method of Fabricating a Composite Blade for a Turbine Engine
Fibrous Structure with Grouping of Floats
Method and Compaction Assembly for Manufacturing a Composite Turbomachine Blade
Method for Designing a Valve and Method for Producing a Valve
Device for Transferring Oil Between Two Repositories Rotating Relative to Each Other, and Propeller Turbomachine for an Aircraft with Such a Device
Turbomachine Part with a Non-Axisymmetric Surface
Monitoring of an Aircraft Engine to Anticipate the Maintenance Operations
Method, System and Computer Program for the Acoustic Analysis of a Machine
Method for Monitoring a Locking System
Method and Device for Measuring Pollutants Contained in Engine Exhaust
Turboprop Air Intake
Fiber Preform for a Hollow Turbine Engine Vane
Application:
15/030,806 →
Publication:
US 2016/0348518
Fiber Preform for a Hollow Turbine Engine Vane
Method for Detecting a Failure in a Motive Flow Valve of an Aircraft Engine Fuel Circuit
Method for Detecting a Failure in a Fuel Return Valve of an Aircraft Engine Fuel Circuit
Turbine Engine Provided with Means for Absorbing Stresses from the Thrust of the Engine Thereof
Technical Trial Method
Device and Method for Replacing Machining Inserts
Technical Testing Method
Sealing System with Two Rows of Complementary Sealing Elements
Method and Device for Characterising a Signal
Annular Element of a Turbomachine Casing
Front Enclosure Which Is Sealed During the Modular Dismantling of a Turbojet with Reduction Gear
Integrated Sintering Process for Microcracking and Erosion Resistance of Thermal Barriers
Application:
15/037,175 →
Publication:
US 2016/0281206
Modular Engine, Such as a Jet Engine, with a Speed Reduction Gear
Lubrication Device for a Turbine Engine
Balanced Turbine Engine Portion and Turbine Engine
Bearing Holder Having a Axisymmetric Sealable Gimlet
Multi-Point Injection Device for an Aircraft Engine
Device for Centring and Guiding the Rotation of a Turbine Engine Shaft Including Improved Means for Retaining the External Bearing Ring
Method and Device for Determining the Wear of a Cutting Tool Flank
Turbomachine Comprising a Shaft Sleeve and Associated Sleeve Tube
Drained fluid evacuation stub for a propulsion assembly
Fan for a Turbomachine
Method for Fixing a Tube to a Connector, and Connecting Kit
Method for Machining a Casing of an Aircraft Turboshaft Engine and Scraper Tool for Implementing Said Method
Method for Determining Tolerance Intervals for Dimensioning a Part
Unducted Fan for an Aircraft Turbine Engine
Rotary Assembly for an Aviation Turbine Engine, the Assembly Comprising a Separate Fan Blade Platform Mounted on a Fan Disk
Blade Made of Organic Matrix Composite Material Provided with a Metal Strip, and a Method of Fastening a Metal Strip on a Blade Fiber Preform
Turbine Ring Assembly with Inter-Sector Connections
Turbine Ring Assembly with Sealing
Turbo-Engine Including Two Separate Ventilation Flows
Sealing Device for an Oil Enclosure in a Turbine Engine Bearing
Guide Device for Variable Pitch Stator Vanes of a Turbine Engine, and a Method of Assembling Such a Device
Device for Retaining Drained Fluids for a Propulsive Assembly
Aircraft Propulsion Assembly with Fire Extinguishing System
Fan, in Particular for a Turbine Engine
Method for Impregnation of a Fibrous Preform and Device for Implementation of the Said Method
Propulsion Assembly Comprising a Box for Retaining Drained Fluids
Torque-Measurement Device for a Turbomachine Shaft
Method for Adhering Parts and Device for Implementing Said Method
Method for Producing a Part by Selective Melting of Powder
Forecasting Maintenance Operations to Be Applied to an Engine
Electroformed Nickel-Chromium Alloy
Cutting Table for Cutting a Fiber Preform Obtained by Three-Dimensional Weaving, and a Cutting Method Using Such a Table
Flow Regulating System for Supplying Propellant Fluid to an Electric Thruster of a Space Vehicle
Turbine Engine Compressor, in Particular of an Aeroplane Turboprop or Turbofan
Device for Cleaning a Turbomachine Module
Aircraft Turbomachine Comprising a Heat Exchanger of the Precooler Type
Method for Manufacturing a Part Coated with a Protective Coating
Blade for a Turbomachine Impeller and Method for Modelling the Same
Guide Arm for Elements Having an Elongated Shape, in Particular for a Turbomachine
Turbomachine Component or Collection of Components and Associated Turbomachine
A Blade, Bladed Wheel, Turbomachine, and a Method of Manufacturing the Blade
Turbomachine Component with Non-Axisymmetric Surface
Annular Combustion Chamber in a Turbine Engine
A Casing Made of Organic Matrix Composite Material That Facilitates the Discharge of Smoke
Method for Producing a Turbine Engine Part, and Resulting Mould and Intermediate Blank
Method for Producing Turbine Engine Parts, and Resulting Mould and Blank Compromising Stacked Parts
Turbomachine Sparkplug Fixing Assembly
Method for Producing Turbine Engine Parts, and Resulting Blank and Mould
Method and Computer Program for the Monitoring of a Thrust Reverser Having Hydraulic Actuators
Epicyclic Reduction Device for the Rotational Drive of Blade Sets of a Reduction Turbomachine
Fire Protection of a Part Made of a Three-Dimensional Woven Composite Material
Fire Protection of a Fan Casing Made of Composite
Mobile Member of a Turbomachine Which Comprises Means for Changing the Resonance Frequency of Same
Turbomachine Bearing Housing
Turbomachine with Collection of a Compressed Air Flow
Turbomachine Casing Comprising a Cavity-Free Shroud and Yokes Reinforced by Stiffeners
Nacelle for an Airplane Turbojet
Blade for a Turbine Engine Propeller, in Particular a Propfan Engine, Propeller, and Turbine Engine Comprising Such a Blade
Forging Tool for the Manufacture of a Shaped Rolled Ring, Notably for the Manufacture of a Turbomachine Disc
Supply of Air to an Air-Conditioning Circuit of an Aircraft Cabin from Its Turboprop Engine
Reduction in the Leakage Flow Rate of a Brush Seal by Flexible Geometric Obstruction
Lever Arm Device for Controlling the Pitch of Fan Blades of a Turbine Engine Having an Unducted Fan
Blade Provided with Platforms Possessing Attachment Portions
Radial Control Shaft for a Device for Controlling the Pitch of Fan Blades of a Turbine Engine Having an Unducted Fan, and a Method of Mounting Such a Shaft
Turbomachine Comprising a Ventilation System
Method and System for Predicting the Operation of an Aircraft by Similarity Analysis Using Distributed Storage and Calculation Capacities
Propulsion Assembly for an Aircraft Having a Turbojet with a Non-Ducted Fan and an Attachment Pylon
Core for the Moulding of a Blade Having Superimposed Cavities and Including a De-Dusting Hole Traversing a Cavity from End to End
Combustion Chamber Comprising Additional Injection Devices Opening Up Directly into Corner Recirculation Zones, Turbomachine Comprising Such a Chamber and Fuel Supply Method for Such a Chamber
Detecting the Clogging of a Fluid Filter
Method for Marking the Surface of a Mechanical Part with a Predefined Graphical Representation Having a Holographic Effect
Heat Treatment of an Alloy Based on Titanium Aluminide
Method for Isolating a Combustible Fluid Tank from a Downstream Portion of a Turbomachine Supply System in Case of a Fire, and Such a Supply System
Application:
15/302,571 →
Publication:
US 2017/0022906
A Shaft Machining Anti-Vibration Device
Method and Device for Remote Endoscopy of an Aircraft Engine
Application:
15/303,169 →
Publication:
US 2017/0030840
Aircraft Turbine Engine with Improved Mechanical Power Takeoff
Related Assignments
(2)
Other recorded transfers of the patents in this record — the chain of ownership.
Assignment of Assignor's Interest
Dec 17, 2012
From: SUIZA, HISPANO
To: SNECMA
Reel/Frame 029481/0429 →
Corrective Assignment to Correct the Cover Sheet to Remove Application Nos. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 Previously Recorded on Reel 046479 Frame 0807. Assignor(S) Hereby Confirms the Change of Name.
Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →