Patent Assignment
Reel/Frame 039300/0039
Change of Name
Recorded: 2016-07-11
Pages: 11
Assignor
ALSTOM TECHNOLOGY LTD
Executed: 2015-11-02
Assignee
GENERAL ELECTRIC TECHNOLOGY GMBH
BROWN BOVERI STRASSE 7, BADEN, 5400, SWITZERLAND
Covered Properties
(111)
Burner
Patent:
5,674,066 →
Application:
08/585,889 →
High-Temperature Probe
Patent:
5,718,512 →
Application:
08/587,972 →
Full Ring Fuel Distribution System for a Gas Turbine Combustor
Patent:
6,282,904 →
Application:
09/443,916 →
Combustion Chamber/Venturi Cooling for a Low Nox Emission Combustor
Patent:
6,446,438 →
Application:
09/605,765 →
Low Nox Emission Combustion Liner with Circumferentially Angled Film Cooling Holes
Patent:
6,427,446 →
Application:
09/664,898 →
Effusion Cooled Transition Duct
Pre-Mix Nozzle and Full Ring Fuel Distribution System for a Gas Turbine Combustor
Patent:
6,446,439 →
Application:
09/706,425 →
Means for Wear Reduction in a Gas Turbine Combustor
Patent:
6,467,272 →
Application:
09/891,003 →
Low Nox Combustion Liner with Cooling Air Plenum Recesses
Patent:
6,430,932 →
Application:
09/909,029 →
Turbine Blade Pocket Shroud
Patent:
6,491,498 →
Application:
09/971,241 →
Wear Reduction Means for a Gas Turbine Combustor Transition Duct End Frame
Combustion Chamber/Venturi Cooling for a Low Nox Emission Combustor
Thermally Free Aft Frame for a Transition Duct
Patent:
6,619,915 →
Application:
10/064,675 →
Transition Duct Mounting System
Patent:
6,662,567 →
Application:
10/064,755 →
Coated Seal Article Used in Turbine Engines
Patent:
6,675,584 →
Application:
10/064,768 →
Advanced Crossfire Tube Cooling Scheme for Gas Turbine Combustors
Fully Premixed Secondary Fuel Nozzle
Fully Premixed Secondary Fuel Nozzle with Dual Fuel Capability
Fully Premixed Secondary Fuel Nozzle with Improved Stability
Fully Premixed Secondary Fuel Nozzle with Improved Stability and Dual Fuel Capability
Insulated Cooling Passageway for Cooling a Shroud of a Turbine Blade
Combustion Chamber/Venturi Configuration and Assembly Method
Transition Duct with Enhanced Profile Optimization
Patent:
6,644,032 →
Application:
10/277,659 →
Effusion Cooled Transition Duct with Shaped Cooling Holes
Advanced Cooling Configuration for a Low Emissions Combustor Venturi
Coated Seal Article with Multiple Coatings
Pressure Ram Device on a Gas Turbine Combustor
Secondary Fuel Nozzle with Readily Customizable Pilot Fuel Flow Rate
Fully Premixed Pilotless Secondary Fuel Nozzle
Gas Turbine Combustor Hybrid Dynamic-Static Probe
Patent:
6,742,394 →
Application:
10/341,573 →
Method of Fuel Nozzle Sizing and Sequencing for a Gas Turbine Combustor
Patent:
6,883,329 →
Application:
10/350,756 →
Convoluted Seal with Enhanced Wear Capability
Turbine Blade Platform Trailing Edge Undercut
Patent:
6,761,536 →
Application:
10/355,883 →
Combustion Liner Cap Assembly Attachment and Sealing System
Transition Duct Support Bracket Wear Cover
Low Emissions Hydrogen Blended Pilot
Coated Crossfire Tube Assembly
Advanced Fuel Nozzle Design with Improved Premixing
Flamesheet Combustor
Turbine Blade Airfoil
Patent:
6,769,878 →
Application:
10/434,691 →
Method of Operating a Flamesheet Combustor
Gas Only Fin Mixer Secondary Fuel Nozzle
Dual Fuel Fin Mixer Secondary Fuel Nozzle
Apparatus and Method for Improving Combustion Stability
Gas Turbine Fuel Pilot Nozzle
Fully Premixed Pilotless Secondary Fuel Nozzle with Improved Tip Cooling
Transition Duct Honeycomb Seal
Vane Enhanced Trailing Edge Cooling Design
Patent:
6,824,352 →
Application:
10/673,311 →
Gas Turbine Combustor End Cover
Turbine Blade Airfoil Having Improved Creep Capability
Cooling and Sealing Design for a Gas Turbine Combustion System
Flow Sleeve for a Law Nox Combustor
Turbine Blade Attachment Lightening Holes
Turbine Blade Shroud Cutter Tip
Primary Fuel Nozzle Having Dual Fuel Capability
Apparatus and Method for Reducing the Heat Rate of a Gas Turbine Powerplant
Transition Duct Apparatus Having Reduced Pressure Loss
Fastened Vane Assembly
Combustion Liner Seal with Heat Transfer Augmentation
Combustion Liner Having Improved Cooling and Sealing
Tornado Torch Igniter
Vane Platform Rail Configuration for Reduced Airfoil Stress
Apparatus and Method for Providing an Off-Gas to a Combustion System
Apparatus and Method for Reducing Carbon Monoxide Emissions
Counter Swirl Shear Mixer
Self-Purging Pilot Fuel Injection System
Combustion Liner with Enhanced Heat Transfer
Shroud Block with Enhanced Cooling
Method of Operating a Combustion System for Increased Turndown Capability
Patent:
7,137,256 →
Application:
10/906,631 →
Seal for a Gas Turbine Engine Having Improved Flexibility
Flashback Suppression System for a Gas Turbine Combustor
Airflow Distribution to a Low Emissions Combustor
Gas Turbine Transition Duct
Turbine Static Structure for Reduced Leakage Air
Inlet Bleed Heat and Power Augmentation for a Gas Turbine Engine
Hook Ring Segment for a Compressor Vane
Vane Platform Rail Configuration for Reduced Airfoil Stress
Stator Damper Shim
Transition Duct Cooling Feed Tubes
Gas Turbine Fuel Nozzle Having Improved Thermal Capability
Low Residence Combustor Fuel Nozzle
Gas Turbine Engine Controls for Minimizing Combustion Dynamics and Emissions
Utilizing Inlet Bleed Heat to Improve Mixing and Engine Turndown
Gas Turbine Integrated with Fuel Catalytic Partial Oxidation
Compressor Airfoil
Transition Duct Assembly
Altering a Natural Frequency of a Gas Turbine Transition Duct
Combustor End Cap Assembly
Combustion Liner Damper
Compound Variable Elliptical Airfoil Fillet
Turbine Blade Platform Trailing Edge Undercut
Axial Retention of a Platform Seal
Shaped Cooling Holes for Reduced Stress
Cooled Gas Turbine Vane Assembly
Application of Dense Vertically Cracked and Porous Thermal Barrier Coating to a Gas Turbine Component
Gas Turbine Transition Duct Profile
Compressor Stator Vane
Compressor Vane Diaphragm
Load Rejection and Recovery Using a Secondary Fuel Nozzle
Stabilizing a Gas Turbine Engine via Incremental Tuning
Tunable Transition Duct Side Seals in a Gas Turbine Engine
Extending Useful Life of a Cobalt-Based Gas Turbine Component
Blade for a Gas Turbine and Casting Technique Method for Producing Same
Application:
12/961,659 →
Publication:
US 2011/0236222
Unflared Compressor Blade
Dynamically Auto-Tuning a Gas Turbine Engine
Turbine Blade Platform Undercut
Employing Fuel Properties to Auto-Tune a Gas Turbine Engine
Selecting and Applying to Fuel-Flow Splits Bias Values to Correct for Elevated Inlet Air Humidity
Turbine Blade Having Improved Flutter Capability and Increased Turbine Stage Output
System and Method for Blade Retention
Component or Coupon for Being Used Under High Thermal and Stress Load and Method for Manufacturing Such Component or Coupon
Application:
13/664,662 →
Publication:
US 2013/0108460
Related Assignments
(7)
Other recorded transfers of the patents in this record — the chain of ownership.
Assignment of Assignor's Interest
Aug 17, 2012
From: POWER SYSTEMS MFG., LLC
To: ALSTOM TECHNOLOGY LTD
Reel/Frame 028801/0141 →
Assignment of Assignor's Interest
Sep 10, 2012
From: ALSTOM
To: ALSTOM TECHNOLOGY LTD
Reel/Frame 028930/0507 →
Assignment of Assignor's Interest
Feb 11, 2017
From: GENERAL ELECTRIC TECHNOLOGY GMBH
To: ANSALDO ENERGIA SWITZERLAND AG
Reel/Frame 041686/0884 →
Assignment of Assignor's Interest
Feb 16, 2017
From: GENERAL ELECTRIC TECHNOLOGY GMBH
To: ANSALDO ENERGIA IP UK LIMITED
Reel/Frame 041731/0626 →
Confirmatory Assignment
May 7, 2021
From: POWER SYSTEMS MFG., LLC
To: ALSTOM TECHNOLOGY LTD.
Reel/Frame 056175/0407 →
Assignment of Assignor's Interest
Jun 1, 2021
From: ANSALDO ENERGIA IP UK LIMITED
To: H2 IP UK LIMITED
Reel/Frame 056446/0270 →
Declaration Confirming Assignment
Jun 2, 2021
From: KRAFT, ROBERT J.
To: POWER SYSTEMS MFG., LLC
Reel/Frame 057089/0629 →