Patent Assignment
Reel/Frame 056446/0270
Assignment of Assignor's Interest
Recorded: 2021-06-01
Pages: 11
Assignor
ANSALDO ENERGIA IP UK LIMITED
Executed: 2021-05-27
Assignee
H2 IP UK LIMITED
27 OLD GLOUCESTER STREET, LONDON, WC1N 3AX, UNITED KINGDOM
Covered Properties
(74)
Effusion Cooled Transition Duct
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 →
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 →
Fully Premixed Secondary Fuel Nozzle with Improved Stability
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
Coated Seal Article with Multiple Coatings
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 →
Flamesheet Combustor
Method of Operating a Flamesheet Combustor
Gas Only Fin Mixer Secondary Fuel Nozzle
Gas Turbine Fuel Pilot Nozzle
Transition Duct Honeycomb Seal
Vane Enhanced Trailing Edge Cooling Design
Patent:
6,824,352 →
Application:
10/673,311 →
Cooling and Sealing Design for a Gas Turbine Combustion System
Flow Sleeve for a Law Nox Combustor
Fastened Vane Assembly
Combustion Liner Seal with Heat Transfer Augmentation
Tornado Torch Igniter
Apparatus and Method for Providing an Off-Gas to a Combustion System
Apparatus and Method for Reducing Carbon Monoxide Emissions
Counter Swirl Shear Mixer
Combustion Liner with Enhanced Heat Transfer
Shroud Block with Enhanced Cooling
Seal for a Gas Turbine Engine Having Improved Flexibility
Flashback Suppression System for a Gas Turbine Combustor
Gas Turbine Transition Duct
Nickel-Base Alloy for Gas Turbine Applications
Turbine Static Structure for Reduced Leakage Air
Stator Damper Shim
Utilizing Inlet Bleed Heat to Improve Mixing and Engine Turndown
Axial Retention of a Platform Seal
Shaped Cooling Holes for Reduced Stress
Cooled Gas Turbine Vane Assembly
Gas Turbine Transition Duct Profile
Compressor Vane Diaphragm
Stabilizing a Gas Turbine Engine via Incremental Tuning
Extending Useful Life of a Cobalt-Based Gas Turbine Component
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
Compressor Blade
Detecting Flashback by Monitoring Engine-Dynamic Spikes
Thermally Free Liner Retention Mechanism
Flamesheet Combustor Dome
Axial Retention of a Platform Seal
Method of Repairing a Transition Duct Side Seal
Anti-Rotation Lug and Splitline Jumper
Compressor Airfoil
Turbine Blade Tip Repair Using Dual Fusion Welding
Stabilizing a Gas Turbine Engine via Incremental Tuning During Transients
Dynamic and Automatic Tuning of a Gas Turbine Engine Using Exhaust Temperature and Inlet Guide Vane Angle
Dynamic Tuning of a Gas Turbine Engine to Detect and Prevent Lean Blowout
Ensuring Non-Excessive Variation of Gradients in Auto-Tuning a Gas Turbine Engine
Combustion Liner with Bias Effusion Cooling
Axially Staged Gas Turbine Combustor with Interstage Premixer
Combustor Dome Damper System
Sealing Device for a Gas Turbine Combustor
Flamesheet Combustor Contoured Liner
Automated Extended Turndown of a Gas Turbine Engine Combined with Incremental Tuning to Maintain Emissions and Dynamics
Flow Control Device for Rotating Flow Supply System
Leading Edge Cooling Channel for Airfoil
Tapered Cooling Channel for Airfoil
Fuel Injection Locations Based on Combustor Flow Path
Gas Turbine Fuel Components
Related Assignments
(3)
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 →
Change of Name
Jul 11, 2016
From: ALSTOM TECHNOLOGY LTD
To: GENERAL ELECTRIC TECHNOLOGY GMBH
Reel/Frame 039300/0039 →
Assignment of Assignor's Interest
Feb 16, 2017
From: GENERAL ELECTRIC TECHNOLOGY GMBH
To: ANSALDO ENERGIA IP UK LIMITED
Reel/Frame 041731/0626 →