Patent Assignment
Reel/Frame 046127/0021
Change of Name
Recorded: 2018-05-11
Pages: 6
Assignor
TURBOMECA
Executed: 2016-05-10
Assignee
SAFRAN HELICOPTER ENGINES
BORDES 64510, FRANCE
Covered Properties
(130)
Process for Making a Heat Resistant Nickel-Base Polycrystalline Superalloy Forged Part
Patent:
6,068,714 →
Application:
09/061,570 →
Variable-Throat Gas-Turbine Combustion Chamber
Patent:
6,263,663 →
Application:
09/330,199 →
Turbomachine Including a Device for Suppressing Vibration Caused by Acoustical Resonance
Device and Method for Adjusting the Power of a Power Pack Driving a Helicopter Rotor
Device and Method for Injecting a Liquid Fuel into an Air Flow for a Combustion Chamber
Helicopter Gas Turbine Engine with Sound Level Lowered by Ejector Hush Kitting
Device for Silencing a Helicopter Gas Turbine Engine and Engine Thus Obtained
Coupling System Including a Safety Fastener Device
Power Generation System for an Aircraft Using a Fuel Cell
Pre-Signaling Magnetic Plug
Device for De-Icing the Air Intake of a Gas Turbine
Assistance Device for Transient Acceleration and Deceleration Phases
Turbine Engine Including a Reversible Electric Machine
Device for Measuring the Torque Transmitted by a Power Shaft
Compressor Impeller Blade with Variable Elliptic Connection
Compressor Cover for Turbine Engine Having Axial Abutment
Hollow Turbine Wheel Vane Comprising a Rib and Associated Wheel and Turbomachine
Diffuser Having Blades with Apertures
Ring Segment Positioning Member
Turbine Wheel Provided with an Axial Retention Device That Locks Blades in Relation to a Disk
Turbine Wheel with an Axial Retention System for Vanes
Soundproof Exhaust Pipe for a Turbine Engine
Thermoelectric Generation for a Gas Turbine
Erosion Indicator for a Compressor Wheel
Axial Centrifugal Compressor with Scalable Rake Angle
Application:
13/256,371 →
Publication:
US 2011/0318188
Turbine Wheel Having De-Tuned Blades and Including a Damper Device
Air Bleed Having an Inertial Filter in the Tandem Rotor of a Compressor
Data Structure for a List of Parts
Device for Supporting a Turbine Ring, Turbine Having Such a Device, and Turbine Engine Having Such a Turbine
Turboshaft Engine with Parallel Shafts
Fuel Flowmeter Having an Improved Regulator Device
Device for Filtering the Intake Air of an Internal Combustion Engine Having Ventilation Means
Turbine Wheel Fitted with an Axial Retaining Ring That Locks the Blades Relative to a Disk
Method for Protecting the Passage of Air in a Drive Part Coupling in an Unprotected Environment, Coupling for Implementation, and Rotor Line Fitted with Such Couplings
Multi-Pierced Combustion Chamber with Counter-Rotating Tangential Flows
Injector Device and Combustion Chamber for a Turbomachine Provided with Such Injector Device
Gas-Guiding Pipe Comprising a Noise-Attenuating Covering with Variable Porosity
Vertical Shaft Turbomachine
Flexible Rear Bearing Mounting, Having an Abutment, for a Turbine Engine
Method for Adapting the Air Flow of a Turbine Engine Having a Centrifugal Compressor and Diffuser for Implementing Same
Application:
13/640,978 →
Publication:
US 2013/0034425
Device for Multipoint Acquisition/Distribution of Fluid, in Particular Probe for Tapping Pressure in a Turbomachine Air Inlet
Non-Lubricated Architecture for a Turboshaft Engine
Method for Dynamically Absorbing Shocks in a Power Shaft, in Particular a Supercritical Shaft, and Shock-Absorbing Architecture for Implementing Said Method
Heat-Exchange Architecture Built into the Exhaust of a Turbine Engine
System for Real Time Simulation of the Environment of an Aeroengine
Method and Architecture for Recombining the Power of a Turbomachine
Method for the Induction Brazing of Parts Having Complex Shapes, and Single or Multiple Brazing Station for Implementing Same
Device for Controlling Pivotable Vanes of a Turbo-Machine
Method for Optimizing the Operability of an Aircraft Propulsive Unit, and Self-Contained Power Unit for Implementing Same
Method for Mountng Shielding on a Turbine Casing, and Mounting Assembly for Implementing Same
Method for Optimizing the Control of a Free Turbine Power Package for an Aircraft, and Control for Implementing Same
Method for Optimizing the Overall Energy Efficiency of an Aircraft, and Main Power Package for Implementing Same
Coupling System Including a Safety Fastener Device
Method of Optimizing the Specific Fuel Consumption of a Twin Engine Helicopter and Twin Engine Architecture with Control System for Implementing It
Application:
13/879,829 →
Publication:
US 2013/0219905
Method for Attaching the Cover of a Centrifugal Compressor of a Turbine Engine, Compressor Cover Implementing Same and Compressor Assembly Provided with Such a Cover
Lubricating Device Having a Bypass Valve
Method for Controlling the Generation of Electricity Applied to an Aircraft Gas Turbine, and Device Implementing Such a Method
Mechanical Protection Method and Device Including a Transmission Shaft Rotating at a Forward Whirl Critical Speed of Rotation
Application:
13/977,924 →
Publication:
US 2013/0280098
Method for Starting a Turbomachine
Method and Device for Supplying a Lubricant
Application:
13/980,696 →
Publication:
US 2014/0075916
Injector for the Combustion Chamber of a Gas Turbine Having a Dual Fuel Circuit, and Combustion Chamber Provided with at Least One Such Injector
Turbomachine Comprising a Privileged Injection Device and Corresponding Injection Method
Method for Calibrating a Torsion Torquemeter
Mechanical Protection Device
Gas Turbine Diffuser Blowing Method and Corresponding Diffuser
Method for Rationalising a Chain of Electrical Components of an Aircraft, Implementation Architecture and Corresponding Aircraft
Centrifugal Compressor Impeller
Air Conditioning System for an Aircraft Passenger Compartment
Variable-Pitch Nozzle for a Radial Turbine, in Particular for an Auxiliary Power Source Turbine
Application:
14/122,490 →
Publication:
US 2014/0147278
Annular Combustion Chamber of a Turbomachine
A Two-Spool Design for a Turboshaft Engine with a High-Pressure Compressor Connected to a Low-Pressure Turbine
Method for Injecting Fuel into a Combustion Chamber of a Gas Turbine, and Injection System for Implementing Same
Method of Diffusing a Gas Turbine Compression Stage, and Diffusion Stage for Implementing Same
Application:
14/126,989 →
Publication:
US 2014/0133957
A Method of Starting a Turbomachine While Reducing Thermal Unbalance
Device for Electrically Powering an Aircraft on the Ground
Combustion Chamber Wall
Pinion Vibration Damping Using Viscoelastic Patch
Application:
14/343,658 →
Publication:
US 2014/0216191
Centrifugal Compressor Provided with a Marker for Measuring Wear and a Method of Monitoring Wear Using Said Marker
Annular Wall of a Combustion Chamber with Improved Cooling at the Level of Primary and/or Dilution Holes
Method and Architecture for Recovery of Energy in an Aircraft
Turbine Engine Comprising an Electrically Activated Fuel Supply Pump, and Turbine Engine Fuel Supply Method
Method and System for Regulating Power in the Event of at Least One Aircraft Engine Failure
Method for Discharging Exhaust Gas from a Gas Turbine and Exhaust Assembly Having Optimised Configuration
Bearing Support for a Hot Section of a Turboshaft Engine, and an Associated Turboshaft Engine
Method and System for the Emergency Start-Up of an Energy Generator Set
Method and Architecture for the Optimized Transfer of Power Between an Auxiliary Power Motor and the Main Engines of a Helicopter
Method and Configuration for an Auxiliary Power Engine to Deliver Propulsive and/or Non-Propulsive Energy in a Helicopter Architecture
Filler Device for a Fluid Tank
Helicopter Engine Air Intake with Increased Bypass Flow
Dual-Circuit Modular Injection Tube
Drainage Method and Purge Collector of a Carburation System of a Helicopter
Accessory Drive Gearbox for Controlling the Flaps of an Aircraft
Method of Determining the Non-Propagation Threshold of Fatigue Cracks at High Frequency
Method and System for Starting an Aircraft Turboengine
Turbine Engine Combustion Assembly with a Variable Air Supply
Two-Circuit Injector for a Turbine Engine Combustion Chamber
Supply and Drain Device for an Injector
Rotor-Stator Assembly for a Gas Turbine Engine
Compression Assembly for a Turbine Engine
Sealing Assembly for Turbomachine
Laser Welding Head and Process
Device and Method for Temporarily Increasing Power
Turbo Machine Combustion Assembly Comprising an Improved Fuel Supply Circuit
Application:
14/764,152 →
Publication:
US 2015/0369489
Broach and Method for Broaching Slots for Parts Such as Turbine Rotor Disks or Turbomachine Compressor Disks
Application:
14/764,894 →
Publication:
US 2015/0375312
Method for Monitoring a Degree of Clogging of the Starting Injectors of a Turbine Engine
Metering Device for a Fuel Feed Circuit of an Engine
Application:
14/773,569 →
Publication:
US 2016/0017817
Turbine Ring for a Turbomachine
Radial or Mixed-Flow Compressor Diffuser Having Vanes
Device for Washing a Turbomachine Air Intake Casing
Application:
14/787,958 →
Publication:
US 2016/0069209
Hybrid Cutoff Member for an Electric Circuit
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
Turbomachine Comprising a Casing Wear Indicator
Ignition Device for an Aircraft Engine
Method for the Monitoring of a Degree of Coking at Seals by a Gas Generator Shaft
Method for Optimizing the Control of a Free Turbine Power Package for an Aircraft, and Control for Implementing Same
Monitoring of a Degree of Coking at Dynamic Seals by a Starter
Turbomachine Designed to Operate in Turning Gear Mode
Method for Optimising the Specific Consumption of a Twin Helicopter
Application:
15/025,456 →
Publication:
US 2016/0237917
Turbomachine Designed to Operate in Turning Gear Mode
Turbine Engine and Control Method
Bladed Rotor
Method and a System for Reliably Starting a Turbine Engine
Device for Draining Liquids for an Aircraft Engine
Method for Automatically Controlling the Operating Speed of a Helicopter Turboshaft Engine, Corresponding Control Device and Helicopter Provided with Such a Device
Endoscope and Method for Using Same
Application:
15/105,497 →
Publication:
US 2017/0006201
Method of Treatment Against Corrosion and Against Wear
Assembly for Turbine Engine for Measuring Vibrations Sustained by a Rotating Blade
Self-Contained Power Unit for Implementing a Method for Optimizing the Operability of an Aircraft Propulsive Unit
Aircraft Engine Comprising Azimuth Setting of the Diffuser with Respect to the Combustion Chamber
Application:
15/302,807 →
Publication:
US 2017/0038075
Related Assignments
(2)
Other recorded transfers of the patents in this record — the chain of ownership.