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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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Heat shield with axial retention lock
United Technologies Corporation
October 12, 2017 - N°20170292704

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. ...
Gas turbine engine variable porosity combustor liner
Rolls-royce Corporation
October 12, 2017 - N°20170292703

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal ...
Heat shield with axial retention lock
United Technologies Corporation
October 12, 2017 - N°20170292702

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support ...
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Gas Turbine Engine Patent Applications
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Airfoil
United Technologies Corporation
October 12, 2017 - N°20170292530

The present disclosure provides methods and systems for an airfoil of a gas turbine engine. An airfoil of a gas turbine engine may comprise an airfoil body having a body contact surface, and an airfoil edge coupled to the body contact surface, wherein at least one of the airfoil body or airfoil edge comprises a fiber metal laminate.
Thrust reverser actuator
Goodrich Actuation Systems Limited
October 12, 2017 - N°20170292474

An actuator operable to drive a thrust reverser in a gas turbine engine, wherein the thrust reverser comprises first and second translatable sleeves. The actuator comprises a first actuating member moveable so as to translate the first sleeve and a second actuating member moveable so as to translate the second sleeve. The actuator further comprises an interlock arrangement operable in ...
Aircraft gas turbine engine nacelle
Rolls-royce Plc
October 12, 2017 - N°20170292473

An aircraft gas turbine engine nacelle comprises a thrust reversal arrangement. The thrust reversal arrangement comprises at least first and second circumferentially spaced fixed thrust reverser cascade boxes each comprising a plurality of thrust reverser vanes configured to direct air forwardly and circumferentially and at least one inter-leaved translating circumferential turning vane configured to direct air in a direction having ...
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.
Retention device for speed change mechanism in a gas turbine engine
United Technologies Corporation
October 12, 2017 - N°20170292454

A gear system for a gas turbine engine includes a carrier that includes a first axial face. A plurality of gears are located in the carrier. An opening in the first axial face of the carrier is aligned with one of the plurality of gears. A housing includes a central cavity and is attached to the first axial face of ...
Gas turbine engine service tube mount
General Electric Company
October 12, 2017 - N°20170292449

An apparatus and method of biasing a service tube within a turbine rear frame of a gas turbine engine. The engine includes an engine core having a service fitting. A service tube is mounted to the service fitting and at least one support mount secures the service tube to the engine core. A spring element on the support mount can ...
Foreign object damage screen for gas turbine system
General Electric Company
October 12, 2017 - N°20170292448

A system includes a foreign object damage (fod) screen configured to be disposed upstream of an air intake of a gas turbine engine and to keep debris from entering the air intake. The fod screen is configured to extend across a fluid flow path extending through the air intake into the gas turbine engine. The fod screen includes a flexible, ...
Hybrid electric aircraft with rankine cycle heat recovery system
Hamilton Sundstrand Corporation
October 12, 2017 - N°20170292447

A propulsion system includes a gas turbine engine, an electric motor system having a motor drive electrically connected to the electric machine and an electric motor electrically connected to the motor drive where the electric motor drives a propulsion unit, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, an energy ...
Use of gas turbine heated fluid for reductant vaporization
General Electric Company
October 12, 2017 - N°20170292424

A system includes a gas turbine engine that may combust a fuel to generate power and an exhaust gas, an exhaust gas path in fluid communication with the gas turbine engine and that may receive the exhaust gas from the gas turbine engine, and a reductant skid fluidly coupled to the exhaust gas path. The reductant skid includes an injection ...
Impingement plate with stress relief feature
Rolls-royce Corporation
October 12, 2017 - N°20170292407

An impingement plate adapted for use in a gas turbine engine is disclosed. The plate includes a plurality of holes for directing cooling air. The plate includes a stress relief feature to prevent fatigue cracking at the coupling of the plate to the turbine engine and at the holes.
Method and apparatus for adjusting variable vanes
United Technologies Corporation
October 12, 2017 - N°20170292400

According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring ...
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.
Integrated brush seals
United Technologies Corporation
October 12, 2017 - N°20170292395

An engine component for a gas turbine engine includes a main body and a plate. The engine component also includes a plurality of wire bristles disposed between the plate and the main body. A joint connects both the plate and the wire bristles to the main body and the joint is configured to prevent gas leakage between the main body, ...
Tangential on-board injectors for gas turbine engines
United Technologies Corporation
October 12, 2017 - N°20170292393

A tobi for a gas turbine engine having a tobi body, a first tobi airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge, and a second tobi airfoil circumferentially adjacent to the first tobi airfoil, the second tobi airfoil having a radially extending portion extending from a leading ...
Turbomachine component, particularly a gas turbine engine component, with a cooled wall and a method ...
Siemens Aktiengesellschaft
October 12, 2017 - N°20170292389

A turbomachine component, particularly a gas turbine engine component, has at least one part built in parts from a curved or planar panel, particularly a sheet metal, the part having a plurality of cooling channels via which a cooling fluid, particularly air, is guidable, wherein at least one of the plurality of cooling channels has a continuously tapered section. The ...
Wrapped serpentine passages for turbine blade cooling
Solar Turbines Incorporated
October 12, 2017 - N°20170292386

A turbine blade for a gas turbine engine may include at least two wrapped, serpentine-shaped internal cooling paths. A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine ...
Rotation enhanced turbine blade cooling
Solar Turbines Incorporated
October 12, 2017 - N°20170292385

A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge ...
System and method for in situ balancing of a rotating component of a gas turbine ...
General Electric Company
October 12, 2017 - N°20170292380

Methods for performing in situ balancing of an internal rotating component of a gas turbine engine are provided. The method can include inserting a repair tool through an access port of the gas turbine engine with the repair tool including a tip end positioned within the gas turbine engine and a material supply end positioned outside the gas turbine engine. ...
Hybrid electric aircraft propulsion incorporating a recuperated prime mover
Hamilton Sundstrand Corporation
October 12, 2017 - N°20170291712

A hybrid-electric propulsion system includes a gas turbine engine, an electric machine coupled to and rotatably driven by the gas turbine engine to produce ac electric power, an energy storage system, and a propulsion unit. The gas turbine engine includes a combustor and a recuperator that places an exhaust air flow that is downstream from the combustor in a heat ...
Method and computer-readable model for additively manufacturing injector assembly or ducting arrangement including such injector ...
Siemens Energy, Inc.
October 05, 2017 - N°20170284676

Method and computer-readable model for additively manufacturing an injector assembly or a ducting arrangement including such assembles, as may be used in a combustion system of a gas turbine engine. The injector assembly may include a reactant-guiding structure (42) that may be configured to define a curvilinear flow path (47) to route a flow of reactants from a first flow direction (50) to ...
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