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Gas Turbine Engine patents

      

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




 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


 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.


 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


 Flux mediated deposition of metallic glass patent thumbnailnew 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.


 Ceramic coating polishing method patent thumbnailnew 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 patent thumbnailCombustor 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

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

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.. .

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

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

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

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

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.

Fuel nozzle with flexible support structures

A fuel nozzle apparatus for a gas turbine engine includes: a fuel discharge element having a discharge orifice communicating with a fuel supply connection; a static supporting structure; and a cantilevered flexible support structure interconnecting the supporting structure and the fuel discharge element, the flexible support structure having a first end connected to the static supporting structure, and a second end connected to the fuel discharge element.. .
General Electric Company

Gas turbine engine combustor liner panel with synergistic cooling features

A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin..
United Technologies Corporation

Combustor tile

A gas turbine engine includes a combustor having a combustor tile assembly with improved cooling air flow channels and enhanced cooling efficiency. A method of manufacturing same is provided which increases production capabilities and the geometric configurations of the exit ports which in turn improve the hot side operating temperature of the tiles in the combustion chamber..
Rolls-royce Corporation

Cooled compressor

An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions.
United Technologies Corporation

System for measuring air mass flow into a gas turbine

A method for measuring air mass flow into a compressor section of a gas turbine engine is provided. Air is introduced into a chamber upstream from an inlet of the compressor section.
Siemens Energy, Inc.

Seals for gas turbine engine nacelle cowlings

A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core.
United Technologies Corporation

Air cooled air cooler for gas turbine engine air system

An air-to-air cooler has a heat exchanger integrated to a housing. A first passage extends through the housing for directing a flow of cooling air through the heat exchanger.
Pratt & Whitney Canada Corp.

Auxiliary oil system for geared gas turbine engine

A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system.
United Technologies Corporation

Advanced distributed engine architechture - design alternative

A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor.
United Technologies Corporation

Guide vane of a gas turbine engine, in particular of an aircraft engine

A guide vane of a gas turbine engine, in particular of an aircraft engine, which has a pressure-side wall, a suction-side wall, a guide vane root, a guide vane tip, a guide vane leading edge area that is impinged by a cooling air flow of a cooling system, a guide vane trailing edge area that is facing away from the guide vane leading edge area, and at least one channel for conducting a fluid to be cooled arranged in an internal space of the guide vane. At that, during operation of the gas turbine engine, a first part of the cooling air flow flows around a pressure-side wall, and a second part of the cooling air flow flows around the suction-side wall, and a third part of the cooling air flow flows through the internal space including the channel.
Rolls-royce Deutschland Ltd & Co Kg

Nacelle compression rods

A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine.
Rohr, Inc.

Method of controlling a position actuation system component for a gas turbine engine

A method for controlling a position actuation system component in a gas turbine engine based on a modified proportional and integral control loop is provided. The method includes determining an error value between a demand signal for the position actuation system component and a position signal for the position actuation system component.
General Electric Company

Break-in system for gapping and leakage control

A blade outer air seal for use in a gas turbine engine having an axis of rotation includes a main body having a mating face configured to face, be positioned radially outward from, and be positioned adjacent to a rotor blade of the gas turbine engine. The blade outer air seal also includes an axial member extending aft from the main body, having a first radial face configured to face a second radial face of an outer diameter platform of a stator of the gas turbine engine, and having a first abradable material coupled to the first radial face..
United Technologies Corporation

Seal for a gas turbine engine

A gas turbine engine assembly includes a shield that has a first portion and a second portion. The first portion extends radially from an axial end portion of the shield and includes a blade outer air seal contact surface.
United Technologies Corporation

Axial transfer tube

What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section.
United Technologies Corporation

Gas turbine engine airfoil squealer pocket cooling hole configuration

A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction.
United Technologies Corporation

Gas turbine engine airfoil with bi-axial skin core

An airfoil for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls that extend from a leading edge to a trailing edge in a chord-wise direction.
United Technologies Corporation

Tip shrouded high aspect ratio compressor stage

A gas turbine engine compressor stage includes a rotor. Compressor blades are supported by the rotor.
United Technologies Corporation

Aircraft engine nacelle

A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells.
Rolls-royce Plc

Vibratory mass media fixture with tip protector

A fixture assembly includes a frame with a tip rail displaced from a main body. A method of polishing a gas turbine engine component includes restricting a flow of media adjacent to a tip of a component with an airfoil to be generally equal to a flow of media adjacent to a sidewall of the airfoil..
United Technologies Corporation

Gas turbine engine wall assembly interface

A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell.
United Technologies Corporation

Gas turbine engine with selective flow path

A gas turbine engine includes a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. There is a duct located downstream of the gas generator.
United Technologies Corporation

Combustion systems

A combustor for a gas turbine engine includes an inner combustor wall and an outer combustor wall radially outboard of the inner combustor wall. The inner and outer combustor walls define a combustion space therebetween with an upstream inlet and a downstream outlet.
Delavan Inc

Rounded edges for gas path components

A gas turbine engine section has a housing and a plurality of panels attached to the housing. The panels face toward a flow path of hot products of combustion.
United Technologies Corporation

Efficient, low pressure ratio propulsor for gas turbine engines

A gas turbine engine includes a gear assembly, a bypass flow passage, and a core flow passage. The bypass flow passage includes an inlet.
United Technologies Corporation

Exhaust nozzle control for a gas turbine engine

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path.
United Technologies Corporation

Shroudless adaptive fan with free turbine

A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the combustor. The first turbine section includes a low pressure turbine that drives the first fan section.
United Technologies Corporation

Combustion systems

A combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome.
Delavan Inc

Core assembly for gas turbine engine

A core assembly includes a core that includes an exterior surface that has a recessed area that extends along the exterior surface. An insert includes a contact surface that corresponds to the recessed area..
United Technologies Corporation

Geared turbofan with independent flexible ring gears and oil collectors

A geared turbofan engine includes a fan rotatable about an engine axis. A compressor section compresses air and delivers the compressed air to a combustor where the compressed air is mixed with fuel and ignited to drive a turbine section that in turn drives the fan and the compressor section.
United Technologies Corporation

Lubricant valve monitoring method and assembly

An exemplary method of monitoring a position of a lubricant valve in a gas turbine engine includes monitoring a position of a lubricant valve using a first auxiliary pressure reading and a second auxiliary pressure reading. The first auxiliary pressure reading is taken when a primary lubrication circuit is at a first pressure.
United Technologies Corporation

Gas turbine engine

A gas turbine engine is provided defining a radial direction. The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath.
General Electric Company

Pump for a turbine engine

A pump for a gas turbine engine is provided. The pump includes a first drive track having a spline and a first gear each rigidly attached to a first driveshaft.
General Electric Company

Turbine shroud segment with integrated cooling air distribution system

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine..
Rolls-royce Corporation

Trunnion retention for a turbine engine

A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk.
General Electric Company

Variable vane actuation system

An example variable vane actuation system of a gas turbine engine includes, among other things, an actuation ring, a plurality of variable vanes circumferentially disposed about an engine axis, a plurality of vane arms configured to actuate the plurality of variable vanes, and a plurality of press fit members coupling the vane arms to the actuation ring.. .
United Technologies Corporation

Turbine shroud segment with load distribution springs

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine..
Rolls-royce Corporation

Turbine shroud segment with buffer air seal system

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine..
Rolls-royce Corporation

Reversible blade rotor seal with protrusions

A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis.
United Technologies Corporation

Turbine shroud segment with flange-facing perimeter seal

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine..
Rolls-royce Corporation

Gas turbine engine component cooling with resupply of cooling passage

A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall.
United Technologies Corporation

Gas turbine engine component platform cooling

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform..
United Technologies Corporation



Gas Turbine Engine topics:
  • Gas Turbine
  • Gas Turbine Engine
  • Downstream
  • High Speed
  • Circulation
  • Heat Exchanger
  • Attenuation
  • Variable Inlet Guide Vanes
  • Variable Inlet Guide Vane
  • Guide Vane
  • Guide Vanes
  • Inlet Guide Vanes


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    This listing is a sample listing of patent applications related to Gas Turbine Engine 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 Engine with additional patents listed. Browse our RSS directory or Search for other possible listings.


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