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Gas Turbine patents

      

This page is updated frequently with new Gas Turbine-related patent applications.




 Calibration block for inspection of gas turbine component and manufacturing method patent thumbnailnew patent Calibration block for inspection of gas turbine component and manufacturing method
A calibration block and method of making the same are disclosed. The block includes a substrate having a base material with first and second opposite sides; a bond layer and a thermal barrier layer coated on the first side of the base material.
General Electric Technology Gmbh


 Acoustic measurement system incorporating a hybrid waveguide providing thermal isolation patent thumbnailnew patent Acoustic measurement system incorporating a hybrid waveguide providing thermal isolation
A gas turbine engine (10) including a hybrid waveguide (84) for placement adjacent a flow path (17) for hot combustion gases in the engine. The waveguide includes first and second opposing ends (88, 90), and comprises a first section (100) formed of a first material extending from a transition region (104) to the first end (88) and a second section (102) formed of a second material extending from the transition region (104) to the second end (90).
Siemens Energy, Inc.


 Combustor assembly for use in a gas turbine engine and  assembling patent thumbnailnew patent Combustor assembly for use in a gas turbine engine and assembling
A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly.
General Electric Company


 Bleed valves for gas turbine engines patent thumbnailnew patent Bleed valves for gas turbine engines
A bleed valve for a gas turbine engine compressor has a valve body and a flapper. The valve body defines a flow path and includes a flapper seat.
Hamilton Sundstrand Corporation


 Gas turbine engine fuel scheduling patent thumbnailnew patent Gas turbine engine fuel scheduling
A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool, a high pressure spool and a fuel metering valve is disclosed. The method comprises scheduling the fuel metering valve in dependence upon the speed of the high pressure spool..
Rolls-royce Plc


 Gas turbine compressing cooling system provided with cooling air supply paths around outer casing patent thumbnailnew patent Gas turbine compressing cooling system provided with cooling air supply paths around outer casing
The present invention relates to a gas turbine which includes a cooling system provided with cooling air supply paths bypassed through an outside casing and, more specifically, to a gas turbine including a cooling system and a cooling method, wherein, in order to supply cooling air to a plurality of turbine blades and other devices provided to the inside of the gas turbine, cooling air supply paths are not provided to the rotor center shaft of the gas turbine but provided around the outer casing of the gas turbine so as to achieve the increased effect in the aerodynamic efficiency of the compressor and the turbine. According to the above structure and method, it may be possible to provide the cooling air supply paths not to the rotor center shaft of the gas turbine but around the outer casing of the gas turbine, thereby finally achieving the increased effect in the aerodynamic efficiency of the compressor and the turbine..
Doosan Heavy Industries & Construction Co., Ltd.


 Acoustic measurement system incorporating a temperature controlled waveguide patent thumbnailnew patent Acoustic measurement system incorporating a temperature controlled waveguide
For a gas turbine engine (10), a method and apparatus for determining temperature of combustion gas in a flow path (17) of the engine. In one embodiment a waveguide (30) includes a cavity (36) with a first waveguide end (32) including a barrier layer (58) which may be a membrane.
Siemens Energy, Inc.


 Power augmentation system for a gas turbine patent thumbnailnew patent Power augmentation system for a gas turbine
A power augmentation system for a gas turbine that is electrically coupled to a power grid incudes, in serial flow order, a compressed air supply, a compressed air storage tank and an expansion turbine that is disposed downstream from the compressed air storage tank. An exhaust outlet of the expansion turbine is in fluid communication with at least one of an inlet section or a compressor of the gas turbine..
General Electric Company


 Gas turbine engine patent thumbnailnew patent Gas turbine engine
A gas turbine engine includes a spool which rotates in use, a static structure and an air bearing, the air bearing being provided at an interface between the spool and the static structure.. .
Rolls-royce Deutschland Ltd & Co Kg


 Shroud assembly for gas turbine engine patent thumbnailnew patent Shroud assembly for gas turbine engine
Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm.
General Electric Company


new patent

Blade or vane row and gas turbine

A blade or vane row including a plurality of blade or vane segments (10), each including a blade or vane body (11), being disposed in a rotational direction to form an annular shape and defining a flow path (r) along which working fluid (g) flows. The blade or vane segments (10) each have an end wall portion (12, 13) that faces the flow path (r) and extends in a rotational direction.
Mitsubishi Hitachi Power Systems, Ltd.

new patent

Flux mediated deposition of metallic glass

A method and resulting gas turbine engine component (40) having a protective layer of metallic glass (14) deposited over a superalloy substrate (12). A further layer of ceramic insulating material (42) may be deposited over the metallic glass.
Siemens Energy, Inc.

new patent

High temperature protective coating

The invention relates to a high temperature protective coating based on mcraly coating, with m at least one element out of the group of ni, co and fe, for a component of a turbo machine, especially a gas turbine, the coating containing at least at least 1.75 vol.-% chromium borides and the coating consisting of the following chemical composition (in wt.-%): 10-27 cr; 3-12 al; 1-4 si; 0.1-3 ta; 0.01-3 y; 0.1-3 b; 0-7 m, with m being a different element out of said group compared to the remainder, and the remainder being m and inevitable impurities. A preferred embodiment is a coating with the following chemical composition: 10-27 cr; 3-12 al; 1-4 si; 0.1-3 ta; 0.01-3 y; 0.1-3 b; 0-7 co and the remainder being ni and inevitable impurities..
Ansaldo Energia Switzerland Ag

new patent

Ceramic coating polishing method

A method of polishing an outer surface of a ceramic coated gas turbine engine component includes applying a rotating diamond brush to the outer surface. The brush is configured to achieve a uniform finish of 150 microinches ra or less over the surface.
United Technologies Corporation

Combustor assembly for a gas turbine engine and making same

A combustor can assembly includes a plurality of combustor cans spaced circumferentially about a gas turbine engine. Each combustor can is coupled in flow communication with at least one fuel manifold via a respective can fuel line.
General Electric Company

Fuel spray nozzle for a gas turbine engine

A fuel spray nozzle comprises a fuel passage (1) having at least one inlet and at least one outlet. The outlet is configured for accelerating fuel exiting the fuel passage into a jet.
Rolls-royce Plc

Cavity staging in a combustor

A combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two annular trapped vortex cavities are located on the combustor liner and staged axially spaced apart.
General Electric Company

Fuel injector

A fuel injection system for a gas turbine engine (10) comprises; a pilot fuel injector section (22, 23) and a main airblast fuel injector section (25, 26, 27, 28, 29), the main airblast fuel injector section having an aft end (29) facing a combustion chamber (30). A surface of the injection system exposed to air flow through an injection system is non-axisymmetric or non-planar in a reference circumferential plane and/or is configured to generate controlled and varying acoustic impedance at or adjacent the aft end where, in use, the air flow collides with an oncoming acoustic wave..
Rolls-royce Plc

Gas turbine

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed..
Ansaldo Energia Switzerland Ag

Gas turbine combustion chamber with integrated turbine inlet guide vane ring as well as manufacturing the same

A gas turbine combustion chamber with an outer combustion chamber wall and an inner combustion chamber wall, wherein the outer combustion chamber wall and the inner combustion chamber wall are respectively formed in one piece with an outer or an inner ring-shaped platform that are connected in one piece with turbine inlet guide vanes which are arranged around the circumference, wherein the gas turbine combustion chamber is mounted only by means of a suspension device that is formed in one piece at the outer platform, as well as a method for manufacturing the same.. .
Rolls-royce Deutschland Ltd & Co Kg

Sealed conical-flat dome for flight engine combustors

A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate.
General Electric Company

Variable exhaust mixer and cooler for a three-stream gas turbine engine

A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure.
United Technologies Corporation

Fuel supply pipeline system for gas turbine

A fuel supply line system used for a gas turbine, including: fuel gas control valves used for controlling delivery to the gas turbine; a first line used for connecting the fuel gas source to the control valves; a second line used for connecting the control valves to the gas turbine; a monitoring device, configured to be used for determining the pressure inside the pipe at the outlet of the second line near said control valve; and a controller, configured to reduce the effective flow area of the pressure control valves or close the control valves when the determined pressure inside the pipe of the second line is greater than a predetermined pressure.. .
Siemens Aktiengesellschaft

Fbo torque reducing feature in fan shaft

Where t represents peak torque during fan blade off, c represents a distance from a centerline of the gas turbine engine to an outer fiber of the fan shaft, j represents a polar moment of inertia of the fan shaft, and τ represents yield stress in shear of the fan shaft.. .

Insulation support system for an exhaust gas system

An insulation support system for an exhaust gas system gas turbine includes an outer casing having an inner surface and a liner sheet having an inner surface and that defines an insulation gap is defined between the inner surface of the liner sheet and the inner surface of the outer casing. The system further includes a support member that extends from the inner surface of the outer casing to the inner surface of the liner sheet and a threaded fastener that is fixedly connected to one of inner surface of the outer casing or the support member.
General Electric Company

Cooled cooling air system for a turbofan engine

An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core.
United Technologies Corporation

Gas turbine engine aft bearing arrangement

An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends.
United Technologies Corporation

Motive air conditioning system for gas turbines

A motive air conditioning system for a gas turbine assembly is provided. The motive air conditioning system may include an inlet flow channel configured to be fluidly coupled with the gas turbine assembly.
Dresser-rand Company

Nacelle anti-ice system and method with equalized flow

A gas turbine engine is provided having a nacelle and a compressor section constructed and arranged to generate hot air. An anti-icing system is constructed and arranged to discharge the hot air from the compressor section to the nacelle.
United Technologies Corporation

Sequential combustor and operating the same

The present invention generally relates to a sequential combustor for a gas turbine having second and/or subsequent stages of a re-heat, sequential or axially-staged combustion system. A variation in mach number along the flow path can be used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion..
Ansaldo Energia Switzerland Ag

Bearing assembly for supporting a rotor shaft of a gas turbine engine

In one aspect, a bearing assembly for supporting a rotor shaft relative to a support structure of a gas turbine engine may generally include a bearing including an outer race and an inner race, an outer bearing housing configured to extend radially between the outer race of the bearing and the support structure of the gas turbine engine and an inner bearing support configured to extend radially between the inner race of the bearing and the rotor shaft. In addition, the outer bearing housing and the inner bearing support each include at least one radially extending spring arm such that the outer bearing housing and the inner bearing support collectively form two springs coupled in series between the support structure and the rotor shaft..
General Electric Company

Mechanical component for thermal turbo machinery

A mechanical component for thermal turbo machinery, such as a steam or gas turbine, includes a base part and at least one additional device being mechanically coupled to the base part in order to influence the vibration characteristic of the base part during operation of the turbo machine. High-cycle fatigue at part-load can be reduced by enabling the mechanical coupling between the base part and the at least one additional device to change with the temperature of the at least one additional device..
Ansaldo Energia Switzerland Ag

Non-contact seal assembly for rotational equipment with linkage between adjacent rotors

An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes a stator, a rotor and a seal assembly.
United Technologies Corporation

Compressor blade or vane having an erosion-resistant hard material coating

A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate.
Siemens Aktiengesellschaft

Gas turbine engine blade with increased wall thickness zone in the trailing edge-hub region

Airfoil outer wall thickness of a gas turbine engine blade is increased in the zone that is proximate the trailing edge and blade hub by forty to sixty percent (40-60%) greater than comparable greatest wall thickness anywhere else along the trailing edge from outboard that zone all the way to the blade tip. The increased thickness zone includes a transition zone that bridges the respective airfoil outer wall thicknesses proximate the hub and tip of the blade.
Siemens Energy, Inc.



Gas Turbine topics:
  • Gas Turbine
  • Gas Turbine Engine
  • Internal Combustion Engine
  • Distributed
  • Combustion
  • Uv Radiation
  • Exhaust Gas
  • Circulation
  • Downstream


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    This listing is a sample listing of patent applications related to Gas Turbine for is only meant as a recent sample of applications filed, not a comprehensive history. There may be associated servicemarks and trademarks related to these patents. Please check with patent attorney if you need further assistance or plan to use for business purposes. This patent data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Gas Turbine with additional patents listed. Browse our RSS directory or Search for other possible listings.


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