Images List Premium Download Classic

Gas Turbine

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


loading
Combustor and gas turbine
Mitsubishi Hitachi Power Systems, Ltd.
October 12, 2017 - N°20170292707

A combustor including a combustor main body having a transition piece that defines a flow channel therein, and a combustor basket inserted in the transition piece from an upstream side of the flow channel that defines a gap through which a film air is sent with an inner peripheral surface of the transition piece; a connecting pipe disposed upstream of ...
Combustion burner, combustor, and gas turbine
Mitsubishi Hitachi Power Systems, Ltd.
October 12, 2017 - N°20170292706

A combustion burner includes a nozzle, a swirl vane having a fuel injection hole, the swirl vane being disposed in an air flow passage of an annular shape extending along an axial direction of the nozzle around the nozzle, and a partition plate having an annular shape and partitioning at least a region of the air flow passage in a ...
Combustor and gas turbine
Mitsubishi Hitachi Power Systems, Ltd.
October 12, 2017 - N°20170292705

A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (p); a plurality of premixing burners (16), each of which has a premixing swirler cylinder (19) and a premixing nozzle (20) disposed inside the premixing swirler cylinder (19) and that are disposed about the axis (p) in the circumferential direction so as to surround the periphery of ...
Gas Turbine Patent Pack
Download 2202+ patent application PDFs
Gas Turbine Patent Applications
Download 2202+ Gas Turbine-related PDFs
For professional research & prior art discovery
inventor
  • 2202+ full patent PDF documents of Gas Turbine-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.
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 ...
Moisture detection system for gas turbine inlet
General Electric Company
October 12, 2017 - N°20170292534

The present application describes a gas turbine inlet air system for providing a flow of air to a compressor. The gas turbine inlet air system may include an inlet air water cooling system positioned upstream of the compressor for cooling the flow of air with a flow of water and a moisture detection system positioned downstream of the inlet air ...
Gas Turbine Patent Pack
Download 2202+ patent application PDFs
Gas Turbine Patent Applications
Download 2202+ Gas Turbine-related PDFs
For professional research & prior art discovery
inventor
  • 2202+ full patent PDF documents of Gas Turbine-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.
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 ...
Flow volume ratio calculation device, control device equipped with same, gas turbine plant equipped with ...
Mitsubishi Hitachi Power Systems, Ltd.
October 12, 2017 - N°20170292458

A gas turbine includes: multiple fuel systems; a combustor that combusts fuels from the multiple fuel systems in compressed air to generate combustion gas; and a turbine that is driven by the combustion gas. A flow volume ratio calculation device which calculates the flow volume ratio of the fuels flowing in the multiple fuel systems includes calculators that receive values ...
Integrated gas turbine inlet silencer and bleed heat system
General Electric Company
October 12, 2017 - N°20170292456

An inlet system for a gas turbine includes an integrated inlet bleed heat system, wherein the inlet bleed design is integrated in, e. G., a silencer or inlet.
Air bypass system for rotor shaft cooling
General Electric Company
October 12, 2017 - N°20170292455

An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a ...
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 Patent Pack
Download 2202+ patent application PDFs
Gas Turbine Patent Applications
Download 2202+ Gas Turbine-related PDFs
For professional research & prior art discovery
inventor
  • 2202+ full patent PDF documents of Gas Turbine-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.
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 ...
Flex-fuel hydrogen reformer for ic engines and gas turbines
Hamilton Sundstrand Corporation
October 12, 2017 - N°20170292446

To improve thermal efficiency of a mobile vehicle or a distributed power generator, portion of the reformate from the storage vessels is used to mix with the primary fuels and air as part of a lean burn fuel mixture for the engine/gas turbine. Also, this on-board flex-fuel h2 reforming apparatus can provide h2 to regenerate the nox and diesel ...
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 ...
Thermal lifting member for blade outer air seal support
United Technologies Corporation
October 12, 2017 - N°20170292398

Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured ...
Loading