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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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Tool and method for decoupling cross-fire tube assemblies in gas turbine engines
General Electric Company
April 12, 2018 - N°20180100654

A tool for decoupling a telescoping tube from a first liner of a gas turbine engine is disclosed. The tool includes a rod partially positioned in a telescoping tube passage. The rod includes a first portion having a non-circular cross-section and a threaded second portion positioned in a second combustion chamber. A plug couples to the rod and engages a ...
Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device
Ansaldo Energia Switzerland Ag
April 12, 2018 - N°20180100651

A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder ...
Bleed valve assembly for a gas turbine engine
General Electric Company
April 12, 2018 - N°20180100441

A gas turbine engine includes a first compressor, a casing surrounding the first compressor, and a liner extending forward from the first compressor. The gas turbine engine also includes a core turbine frame assembly extending between the liner and the casing and a bleed air assembly. The bleed air assembly includes a bleed valve positioned in the liner, and a ...
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Gas Turbine Engine Patent Applications
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Gas turbine engine
General Electric Company
April 12, 2018 - N°20180100435

A gas turbine engine includes a low pressure compressor and a low pressure turbine, with a low pressure shaft coupled to the low pressure turbine through a turbine extension and coupled to the low pressure compressor through a compressor extension. A forward bearing assembly supports the low pressure shaft within a compressor section and at a location aft of the ...
Component assembly for a gas turbine engine
General Electric Company
April 12, 2018 - N°20180100433

A component assembly for a gas turbine engine having a combustor and defining a core air flowpath includes a first wall and a second wall. The first wall is configured for at least partially defining the core air flowpath at a location downstream of a combustion chamber defined by the combustor of the gas turbine engine. Additionally, the second wall ...
Gas turbine engine
General Electric Company
April 12, 2018 - N°20180100410

A gas turbine engine includes a fan section and a core turbine engine operable with the fan section. The gas turbine engine also includes a sump pressurization assembly including a valve, a first duct in airflow communication with the valve and a first pressurized air source, and a second duct in airflow communication with the valve and a second pressurized ...
Gas Turbine Engine Patent Pack
Download 1617+ patent application PDFs
Gas Turbine Engine Patent Applications
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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.
Seals for a gas turbine engine
Rolls-royce North American Technologies, Inc.
April 12, 2018 - N°20180100405

A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to ...
Stator assembly for a gas turbine engine
Rolls-royce Plc
April 12, 2018 - N°20180100403

A stator assembly comprises an annular platform (1) defining a boundary of an annulus and a plurality of guide vanes (2) for arranging in a circumferential array on the annular platform (1). The platform (1) includes a circumferential array of slots each slot having, at a first end, walls converging (3) from an annulus facing side towards an opposite side of the platform and then ...
Method for manufacturing components for gas turbine engines
General Electric Company
April 12, 2018 - N°20180100210

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with ...
Method for producing drilled cooling holes in a gas turbine engine component
Xiamen University
April 12, 2018 - N°20180099360

A method for accurately producing the drilled hole in a wall of a component fabricated by investment casting process, such as for use in a blade or steam turbine includes the following steps. The 3d data of actual component is obtained from the measurements or from the numerical simulation. The actual model and the ideal model are aligned and compared, ...
Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
United Technologies Corporation
April 05, 2018 - N°20180094817

An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased circumferential fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a ...
Injector resonator for a gas turbine engine
Solar Turbines Incorporated
April 05, 2018 - N°20180094816

A fuel injector for a combustor of a gas turbine engine is disclosed herein. In embodiments, the fuel injector includes an injector head, a stem, a fuel passage, a fitting, a fuel inlet, and a resonator. The stem extends from the injector head. The fuel passage extends within the towards the injector head. The fitting is joined to the stem ...
Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
United Technologies Corporation
April 05, 2018 - N°20180094814

An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a ...
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.
Integrally bladed fan rotor
Pratt & Whitney Canada Corp.
April 05, 2018 - N°20180094638

An integrally bladed fan (ibf) rotor of a gas turbine engine. The ibf rotor includes a hub and a plurality of fan blades extending radially outwardly from the hub and integral therewith. The hub has a fan attachment flange disposed at an end of the hub on a trailing edge side thereof for mounting a booster rotor to a trailing ...
Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
United Technologies Corporatoin
April 05, 2018 - N°20180094590

Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at ...
Gas turbine engine motoring with starter air valve manual override
United Technologies Corporation
April 05, 2018 - N°20180094588

A system for gas turbine engine motoring includes an air turbine starter coupled to a gearbox of a gas turbine engine and a starter air valve in fluid communication with the air turbine starter to drive motoring of the gas turbine engine responsive to a regulated pressure from a compressed air source. A manual override of the starter air valve ...
Pin insert and igniter assembly
Unison Industries, Llc
April 05, 2018 - N°20180094587

An igniter assembly for an engine, including a gas turbine engine, includes a shell comprising a tip end defining an opening and a sidewall extending away from the tip end where the sidewall surrounds a cavity within the shell and a tip insert assembly operably coupled to the tip end within the opening and having an insert body and a ...
Dual tierod assembly for a gas turbine engine and method of assembly thereof
General Electric Company
April 05, 2018 - N°20180094544

A core engine includes a first tierod and a compressor rotor assembly including a plurality of compressor rotor disks arranged in a face to face orientation and spaced along the first tierod. The core engine includes a second tierod and a turbine rotor assembly including a plurality of turbine rotor disks arranged in a face to face orientation and spaced ...
Flexible support structure for a geared architecture gas turbine engine
United Technologies Corporation
April 05, 2018 - N°20180094541

A gas turbine engine includes a fan shaft is drivingly connected to a fan having fan blades. A gear system is connected to the fan shaft and driven through an input having a gear reduction ratio of greater than 2. 3. A gear system flex mount arrangement accommodates for misalignment of the fan shaft and the input during operation and includes a ...
Flexible support structure for a geared architecture gas turbine engine
United Technologies Corporation
April 05, 2018 - N°20180094540

A gas turbine engine includes a fan that has fan blades. A fan shaft is drivingly connected to the fan. A frame supports the fan shaft and defines a frame lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the ...
Geared architecture for high speed and small volume fan drive turbine
United Technologies Corporation
April 05, 2018 - N°20180094532

A gas turbine engine includes a fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of ...
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