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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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Method of manufacturing and inspecting gas washed components in a gas turbine engine
Rolls-royce Plc
December 07, 2017 - N°20170350683

A method of producing a component having an in use gas washed surface, including: obtaining a reference-component having a reference shape with in use gas washed surface; determining performance-sensitivity-distribution for the reference-component, the performance-sensitivity-distribution having plurality of points, each point indicative of a performance factor for the reference-component; identifying plurality of zones on the reference-component performance-sensitivity-distribution, each zone including at ...
Contoured shroud swirling pre-mix fuel injector assembly
General Electric Company
December 07, 2017 - N°20170350598

The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the outer sleeve, and at least one axially oriented vane defined between the centerbody and a section of the inner sleeve. A section ...
Fuel delivery system and method for a gas turbine engine
General Electric Company
December 07, 2017 - N°20170350323

A gas turbine engine and method of operation are provided. The gas turbine engine may include a variable geometry component operably driven by a component actuator. The component actuator may be in fluid communication with a primary line having a valve associated therewith. The method may include determining a demand pressure associated with actuating the variable geometry component using the ...
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Gas Turbine Engine Patent Applications
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Internal tube oil coke prevention geometry
United Technologies Corporation
December 07, 2017 - N°20170350274

A gas turbine engine includes a bearing compartment with a bottom disposed opposite a top. An outlet is formed in the bottom of the bearing compartment. A seal is positioned between the bottom of the bearing compartment and the top of the bearing compartment. A scavenge line is connected to the outlet. The scavenge line forms a fluid trap that ...
Condensation irradiation system
Rolls-royce Plc
December 07, 2017 - N°20170350272

A condensation irradiation system is disclosed comprising an electromagnetic radiation emitter mounted on a locating structure, the locating structure being arranged in use to position the radiation emitter so as radiation emitted therefrom travels through a condensation detection region adjacent an upstream side of a gas turbine engine fan.
Nozzle cooling system for a gas turbine engine
General Electric Company
December 07, 2017 - N°20170350258

The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement ...
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.
Turbine engine shaft torque sensing
General Electric Company
December 07, 2017 - N°20170350253

A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may ...
Torroidal spinner aft flange
United Technologies Corporation
December 07, 2017 - N°20170349265

A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-torroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to ...
Low noise compressor and turbine for geared turbofan engine
Mitu Aero Engines Ag
November 30, 2017 - N°20170343574

A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction that effects a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of ...
Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion ...
Siemens Energy, Inc.
November 30, 2017 - N°20170343217

A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or ...
Gas turbine engine afterburner
Rolls-royce North American Technologies Inc.
November 30, 2017 - N°20170343215

An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages ...
System for an improved stator assembly
United Technologies Corporation
November 30, 2017 - N°20170343011

An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an od ring, and an id ring. The exit guide vane may couple at one end to the od ring and at an opposite end to the id ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The od ...
Mechanically retained fan blade cover
United Technologies Corporation
November 30, 2017 - N°20170343007

A blade assembly may be configured to rotate about an axis of a gas turbine engine. The blade assembly may include a blade and a blade cover. A blade may include a first surface defining a perimeter of a cavity in the blade. A first portion of the perimeter of the cavity includes a lip. A blade cover disposed over ...
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 delivery system for a gas turbine engine
General Electric Company
November 30, 2017 - N°20170342912

A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to ...
Attachment system for a gas turbine engine
General Electric Company
November 30, 2017 - N°20170342910

The present disclosure is directed to a system for attaching an instrument lead to a gas turbine engine component. The system includes a gas turbine engine component that includes a surface. A first sleeve couples to the surface of the gas turbine engine component. The first sleeve defines a first sleeve passageway extending therethrough. An instrument lead extends through the ...
Split-zone flow metering t-tube
One Financial Plaza
November 30, 2017 - N°20170342904

A gas turbine engine according to an example of the present disclosure includes a fan situated at an inlet of a bypass passage. The fan has a fan diameter, dfan. A low pressure turbine section is configured to drive the fan and a first compressor section. The low pressure turbine section has a greater number of stages than the first ...
Exhaust diffuser
General Electric Company
November 30, 2017 - N°20170342862

The present application provides an exhaust diffuser for a gas turbine engine. The exhaust diffuser may include a hub, a casing, and a strut extending between the hub and the casing. The hub may include an angled configuration about the strut and a substantially flat configuration downstream of the angled configuration.
Flexible support structure for a geared architecture gas turbine engine
United Technologies Corporation
November 30, 2017 - N°20170342858

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear transverse stiffness, at least one journal ...
Twin spool industrial gas turbine engine with variable inlet guide vanes
United Technologies Corporation
November 30, 2017 - N°20170342854

A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low ...
Turbine blade track assembly
Rolls-royce Corporation
November 30, 2017 - N°20170342852

A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine ...
Turbine shroud with full hoop ceramic matrix composite blade track and seal system
Rolls-royce North American Technologies, Inc.
November 30, 2017 - N°20170342849

A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is ...
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