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Gas Turbine Engine

Gas Turbine Engine-related patent applications - as published by the U.S. Patent and Trademark Office (USPTO).


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System and method for performing a visual inspection of a gas turbine engine
General Electric Company
June 15, 2017 - N°20170167953

A method for performing a visual inspection of a gas turbine engine may generally include inserting a plurality of optical probes through a plurality of access ports of the gas turbine engine. The access ports may be spaced apart axially along a longitudinal axis of the gas turbine engine such that the optical probes provide internal views of the gas ...
Method for mounting a combustion chamber of a gas turbine engine
Rolls Royce Deutschland Ltd & Co Kg
June 15, 2017 - N°20170167731

A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to ...
Multiple feed platefins within a hot gas path cooling system in a combustor basket in ...
Siemens Aktiengesellschaft
June 15, 2017 - N°20170167729

A hot gas path cooling system (10) for a combustor of a gas turbine engine, whereby the cooling system (10) is positioned within a combustor basket (18) is disclosed. The cooling system (10) may include a platefin cooling system (24) formed from a platefin member (26) positioned radially inward from an outer wall (28) forming a combustor basket (18). At least first and second cooling circuits (34, 36) may be ...
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Gas Turbine Engine Patent Applications
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Power gearbox pin arrangement
General Electric Company
June 15, 2017 - N°20170167540

A planet gearbox has a planet gear rotatable on a planet bearing that includes an inner ring that is mounted to a carrier of an epicyclic gearing arrangement. A respective cylindrical inner surface of each opposite respective end of the inner ring is non-rotatably connected to a respective cylindrical outer surface of a respective one of a pair of support ...
Gas turbine engine airfoil
United Technologies Corporation
June 15, 2017 - N°20170167503

An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
Inlet bleed heat control system
General Electric Company
June 15, 2017 - N°20170167496

The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient ...
Gas Turbine Engine Patent Pack
Download 1617+ patent application PDFs
Gas Turbine Engine Patent Applications
Download 1617+ Gas Turbine Engine-related PDFs
For professional research & prior art discovery
inventor
  • 1617+ full patent PDF documents of Gas Turbine Engine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
  • Index pages: Table View and Image-Grid View layouts. All images in each PDF.
Fuel control system for a gas turbine engine of an aircraft
Airbus Operations, S.l.
June 15, 2017 - N°20170167391

A fuel control system for a gas turbine engine of an aircraft having an engine gearbox, a fuel tank, and an engine combustion chamber, wherein the system includes a high pressure fuel pump, at least one electrically controlled fuel injector, a fuel pressure and temperature sensors, and a fuel controller coupled with the sensors to calculate the fuel density, the ...
Intercooled cooling air with auxiliary compressor control
United Technologies Corporation
June 15, 2017 - N°20170167388

A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors in the compressor section, passes the tapped air through a heat exchanger and then to a cooling ...
Multi-source turbine cooling air
United Technologies Corporation
June 15, 2017 - N°20170167386

A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a ...
Diffuser mounted fuel-air heat exchanger
United Technologies Corporation
June 15, 2017 - N°20170167385

A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the ...
Compressor core inner diameter cooling
United Technologies Corporation
June 15, 2017 - N°20170167384

A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the ...
Thermal management system
General Electric Company
June 15, 2017 - N°20170167382

A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes one or more heat source exchangers and a deicing module. The one or more heat source exchangers and the deicing module are each in thermal communication with ...
Turbulators for improved cooling of gas turbine engine components
United Technologies Corporation
June 15, 2017 - N°20170167381

A gas turbine engine component includes a body defining a cooling airflow passage thereat configured for directing a cooling airflow therethrough. A plurality of turbulators are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurality of turbulators includes a plurality of facets extending outwardly from a central portion. A gas turbine engine ...
Gas Turbine Engine Patent Pack
Download 1617+ patent application PDFs
Gas Turbine Engine Patent Applications
Download 1617+ Gas Turbine Engine-related PDFs
For professional research & prior art discovery
inventor
  • 1617+ full patent PDF documents of Gas Turbine Engine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
  • Index pages: Table View and Image-Grid View layouts. All images in each PDF.
Meta-stable detergent based foam cleaning system and method for gas turbine engines
General Electric Company
June 15, 2017 - N°20170167290

Embodiments in accordance with the present disclosure include a meta-stable detergent based foam generating device of a turbine cleaning system includes a manifold configured to receive a liquid detergent and an expansion gas, a gas supply source configured to store the expansion gas, and one or more aerators fluidly coupled with, and between, the gas supply source and the manifold. ...
System and method for locating a probe within a gas turbine engine
General Electric Company
June 15, 2017 - N°20170167289

A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also ...
Calibrated turbine engine shaft torque sensing
General Electric Company
June 15, 2017 - N°20170167287

A system for measuring torque for a gas turbine engine shaft is provided. The system can include a torque sensor positioned at an engine shaft. The torque sensor, itself, can include a strain sensor for obtaining a strain measurement of the engine shaft and a temperature sensor for obtaining a temperature measurement of the engine shaft. The system can also ...
System and method for locating a probe within a gas turbine engine
General Electric Company
June 15, 2017 - N°20170167285

A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also ...
Gas turbine engine turbine cooling system
Rolls-royce Plc
June 15, 2017 - N°20170167273

A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum ...
Cooling arrangement
Rolls-royce Plc
June 15, 2017 - N°20170167272

An aerofoil for a gas turbine engine including a pressure wall and a suction wall and defining leading and trailing edge, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an ...
Gas turbine engine component cooling assembly
United Technologies Corporation
June 15, 2017 - N°20170167271

A rotor blade assembly includes at least one rotor blade including an airfoil that has a leading edge internal cooling passage that extends through the rotor blade and is in communication with cooling holes along a leading edge of the airfoil. A compression portion includes a compression passage that is in communication with the leading edge internal cooling passage.
Gas turbine engine airfoil
United Technologies Corporation
June 15, 2017 - N°20170167267

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial leading edge position and span position that defines a curve with a negative slope from 90% span to 100% span. The negative slope corresponds ...
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