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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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Computer implemented methods, apparatus, computer progams and non-tranistory computer readable storage mediums for automatically designing ...
Rolls-royce Plc
February 15, 2018 - N°20180046749

A computer implemented method of automatically designing a secondary air system for a gas turbine engine. The method comprises: receiving a geometry model of at least a part of a gas turbine engine, the geometry model including a plurality of data entities for a plurality of features of the gas turbine engine; defining a plurality of cavities using the plurality ...
Method of facilitating visual detection of a crack in a component of a gas turbine ...
Pratt & Whitney Canada Corp.
February 15, 2018 - N°20180045608

A component of a gas turbine engine comprises a substrate, a corrosion resistant top layer, and an intermediate corrodible layer disposed between the corrosion resistant top layer and the substrate. When corroding, the intermediate layer has a color contrasting with a color of the top layer. A method of detecting a crack when it penetrated the top layer in a ...
Mixer assembly for a gas turbine engine
United Technologies Corporation
February 15, 2018 - N°20180045415

A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
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Gas Turbine Engine Patent Applications
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Strut for an aircraft engine
General Electric Company
February 15, 2018 - N°20180045221

A strut for a gas turbine engine includes a body defining a first side and an opposite second side. The first side is spaced from the second side along the circumferential direction of the gas turbine engine. Additionally, the body includes an inner section, a middle section, and an outer section. Each of the inner, middle, and outer sections are ...
Shim for gas turbine engine
United Technologies Corporation
February 15, 2018 - N°20180045218

A joint for a gas turbine engine includes a first component, a second component, an annular shim disk, and fasteners. The first component has a first ring portion and a first annular radial flange that extends from the first ring portion. The second component has a second ring portion and a second annular radial flange that extends from the second ...
Aircraft gas turbine engine nacelle
Rolls-royce Plc
February 15, 2018 - N°20180045140

An aircraft gas turbine engine nacelle comprising a thrust reversal arrangement. The thrust reversal arrangement comprises at least one thrust reverser cascade box comprising a fixed structure and a plurality of thrust reverser vanes configured to direct bypass air forwardly. At least a subset of the thrust reverser vanes are pivotable and/or translatable relative to the fixed structure between ...
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.
Nose cone assembly and method of circulating air in a gas turbine engine
United Technologies Corporation
February 15, 2018 - N°20180045138

A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.
Fuel pump health detection
Hamilton Sundstrand Corporation
February 15, 2018 - N°20180045122

According to an aspect, a ground-based health test of a fuel pump of a fuel control system of a gas turbine engine is initiated. A starter speed of the gas turbine engine is determined while the ground-based health test is in progress. Fuel flow is initiated from the fuel pump to an ignition system of the gas turbine engine with ...
Gas turbine engine with high speed low pressure turbine section
United Technologies Corporation
February 15, 2018 - N°20180045120

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0. 5 and about 1. 5.
Geared turbofan with low spool power extraction
United Technologies Corporation
February 15, 2018 - N°20180045119

A geared turbofan engine includes a first spool including a first compressor and a first turbine. The first compressor is immediately before a combustor and the first turbine is immediately after the combustor. A second spool includes at least a second turbine disposed axially aft of the first turbine. A first tower shaft is engaged to drive the high speed ...
Modulated turbine component cooling
General Electric Company
February 15, 2018 - N°20180045117

Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow ...
Ice protection system for gas turbine engines
Rolls-royce Corporation
February 15, 2018 - N°20180045116

A gas turbine engine includes devices, systems, and methods for de-icing using heat of compression and expelling the de-icing medium into a gas flow path of the engine.
Multi-circuit buffer system for a gas turbine engine
United Technologies Corporation
February 15, 2018 - N°20180045115

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. 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.
Turbine engine ejector throat control
General Electric Company
February 15, 2018 - N°20180045074

An apparatus and method for providing a pressurized air supply to a balance piston assembly to balance an axial load on a gas turbine engine compressor. The pressurized air supply can be supplied by mixing valve mixing a primary and secondary pressure bleed air supply relative to feedback received from the balance piston assembly to maintain a predetermined pressure at ...
Shaft shear detection in gas turbine engines
Pratt & Whitney Canada Corp.
February 15, 2018 - N°20180045071

There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine. The method comprises determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a ...
Mechanically driven air vehicle thermal management device
General Electric Company
February 15, 2018 - N°20180045068

The present disclosure is directed to an aircraft power generation system including a reverse brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least ...
Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of ...
Siemens Aktiengesellschaft
February 15, 2018 - N°20180045059

An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling ...
Wands for gas turbine engine cleaning
Rolls-royce Corporation
February 15, 2018 - N°20180043400

Wands are used as parts of cleaning systems to conduct cleaning agents into gas turbine engine cores. Wands according to the present disclosure include inlet assemblies adapted to connect to cleaning agents, dispensers adapted to discharge cleaners into gas turbine engines, and conduits that extend from the inlet assemblies to the dispensers.
Combustor panel for gas turbine engine
United Technologies Corporation
February 08, 2018 - N°20180038593

A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate ...
Fan blade with composite cover
United Technologies Corporation
February 08, 2018 - N°20180038386

A fan blade assembly for a gas turbine engine includes a blade body, a blade cover secured to the blade body and an adhesive layer to secure the blade cover to the blade body, the adhesive layer configured to set at ambient temperature. A method of forming a fan blade assembly for a gas turbine engine includes forming a blade ...
Mistuned laminate airfoil
United Technologies Corporation
February 08, 2018 - N°20180038382

A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate ...
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