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Gas Turbine Engine patents

      

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




 Device for mounting a spark plug in a combustion engine of a gas turbine engine patent thumbnailDevice for mounting a spark plug in a combustion engine of a gas turbine engine
A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards.
Snecma


 Combustor for a gas turbine engine patent thumbnailCombustor for a gas turbine engine
In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel.
Rolls-royce Plc


 Planet gearbox with cylindrical roller bearing with under race lube scheme patent thumbnailPlanet gearbox with cylindrical roller bearing with under race lube scheme
A planet gear rotatable on a planet bearing with cylindrical rollers is mounted to a carrier of an epicyclic gearing arrangement. Either the cylindrical outer surface of the support pin or the opposing cylindrical inner surface of the inner ring of the planet bearing includes a network of interconnected grooves.
General Electric Company


 Geared gas turbine engine patent thumbnailGeared gas turbine engine
A gas turbine engine includes gearbox including sun gear, annulus gear, plurality of planet gears and carrier. Each planet gear is rotatably mounted in carrier by bearing.
Rolls-royce Plc


 Compressor patent thumbnailCompressor
A compressor section for a gas turbine engine, the compressor section including a circumferential row of stator vanes, a circumferential row of rotor blades, and a casing arrangement. A row of bleed ports are provided in the casing arrangement.
Rolls-royce Plc


 Thrust scheduling  variable pitch fan engines and turbo-shaft, turbo-propeller engines patent thumbnailThrust scheduling variable pitch fan engines and turbo-shaft, turbo-propeller engines
A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor; receiving a control command from a full authority digital engine control (fadec) in the control system; generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received; generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; and supplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine..
General Electric Company


 Gas turbine with a valve cooling system patent thumbnailGas turbine with a valve cooling system
The present application provides a gas turbine engine. The gas turbine engine may include a compressor air extraction system with a number of valves, an exhaust frame cooling system with an exhaust frame blower, and a turbine valve cooling system with one or more valve protection boxes surrounding one or more of the valves.
General Electric Company


 Systems and methods for wheel space temperature management patent thumbnailSystems and methods for wheel space temperature management
The present application provides a gas turbine engine intended to be used in part in hot ambient conditions. The gas turbine engine may include a compressor, a turbine with a wheel space adjacent to a number of rotor wheels, and a wheel space water cooling system in communication with the wheel space to provide a flow of water thereto..
General Electric Company


 Horizontal engine build stand patent thumbnailHorizontal engine build stand
A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module..
United Technologies Corporation


 Spoke locking architecture patent thumbnailSpoke locking architecture
A spoke locking arrangement comprising a washer seated in a seat defined in a structural ring of a gas turbine engine, the washer having a portion thereof plastically deformed into an anti-rotation notch defined in the structural ring, thereby locking the washer against rotation in the seat, the washer further comprising a set of holes for receiving corresponding bolts, and wherein the washer further has at least one anti-rotation tab at each hole, the anti-rotation tabs being deformable in engagement with the bolts to individually lock the same against rotation.. .
Pratt & Whitney Canada Corp.


Spoke mounting arrangement

A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring..
Pratt & Whitney Canada Corp.

Wheel space purge flow mixing chamber

Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm.
General Electric Company

Shroud assembly for a gas turbine engine

A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber.
General Electric Company

Wheel space purge flow mixing chamber

Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm.
General Electric Company

Systems and methods to facilitate enhancing turbine output using an auxiliary generator

A gas turbine engine system includes a gas turbine engine with a rotating element, at least one primary rotor shaft coupled to the rotating element, and a primary generator coupled to the at least one primary rotor shaft. The system further includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft.
General Electric Company

Shroud assembly for a gas turbine engine

An assembly for mounting a circumferential shroud to a casing, including a plurality of arcuate shroud segments collectively forming the circumferential shroud. Each segment includes a circumferentially extending wall and a channel extending from the wall.
Rolls-royce Plc

Turbine cavity sealing assembly

Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting halo seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane..
United Technologies Corporation

Turbine slotted arcuate leaf seal

A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully.
General Electric Company

Additively manufactured connection for a turbine nozzle

Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band.
General Electric Company

Nozzle for a gas turbine engine

A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber.
General Electric Company

Gas turbine engine with a transition duct and corresponding manufacturing a transition duct

A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile.
Siemens Aktiengesellschaft

Additively manufactured bladed disk

A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone.
General Electric Company

Blade platform gusset with internal cooling

A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform.
United Technologies Corporation

Turbine blade

An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element.
General Electric Company

Turbine blade

An airfoil for a gas turbine engine can receive a flow of cooling fluid through a cooling circuit. The cooling circuit is defined within the airfoil comprising a supply passage and a leading edge cooling passage, the two passages being in fluid communication through a plurality of impingement orifices disposed within a cross-over rib disposed between and at least partially defining the passages.
General Electric Company

Crosswind performance aircraft engine spinner

Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8.
General Electric Company

Aircraft pneumatic system

An aircraft pneumatic system comprises a main gas turbine engine (10) comprising a main compressor (14, 16), a recuperated auxiliary gas turbine engine (40) comprising a core compressor (42) having an inlet in fluid communication with a main compressor bleed (32) of the main gas turbine engine(10) and an environmental control system inlet in fluid communication with the main compressor bleed (32) of the main gas turbine engine (10). The environmental control system comprises a compressor (68) driveable by power provided by the auxiliary gas turbine engine (40)..
Rolls-royce Plc

Exchangeable orifice binary valve

A system includes a fluid valve metering system which regulates a flow of a fluid within a gas turbine engine. The fluid valve metering system includes an inlet manifold, an outlet manifold in fluid communication with the inlet manifold, and multiple fluid conduits extending between the inlet manifold and the outlet manifold.
General Electric Company

Systems and methods for monitoring lubricant film thickness of a journal bearing in an epicyclic gear system of an operating gas turbine engine

Monitoring a thickness of a lubricant film in a journal bearing of an epicyclic gear system in an operating gas turbine engine is provided. The method comprises receiving, by a signal processor from a sensor, an electrical property measurement across the lubricant film.
United Technologies Corporation

Methods and systems for estimating residual useful life of a rolling element bearing

Estimating residual useful life of a rolling element bearing in an operating gas turbine engine is provided. A processor receives a vibration signal from a vibration sensor.
United Technologies Corporation

Flow limiting duct vent valves and gas turbine engine bleed air systems including the same

Embodiments of a flow limiting duct vent valve (dvv) are provided, as are embodiments of a bleed air system including a flow limiting dvv. In one embodiment, the bleed air system a flow limiting dvv and a first valved device, such as a high pressure regulator.
Honeywell International Inc.

Sensor snubber block for a gas turbine engine

A snubber block for a manifold assembly of a gas turbine engine includes a body with at least one passage with a respective flow restrictive orifice, the body operable to receive a sensor and a male section that extends from the body, the male section receivable within a fuel manifold.. .
United Technologies Corporation

Engine components with impingement cooling features

gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface.
General Electric Company

Multi-flow cooling passage chamber for gas turbine engine

A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit.
United Technologies Corporation

Gas turbine engine components, blade outer air seal assemblies, and blade outer air seal segments thereof

A gas turbine engine component is provided. The gas turbine engine component has an internal cooling passage having first endwall and a second endwall.
United Technologies Corporation

Fabric seal and assembly for gas turbine engine

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil.
Rolls-royce Corporation

Low modulus insert for a component of a gas turbine engine

A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void.
General Electric Company

Variable pitch fan blade retention system

A variable pitch fan for a gas turbine engine includes a fan blade defining a pitch axis and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment.
General Electric Company

Fan platform for a gas turbine engine

A gas turbine including a fan platform positioned between adjacent fan blades of a fan of the gas turbine engine is provided. The fan platform defines an outer surface that at least partially defines an inner flowpath boundary of the fan.
General Electric Company

Cooling holes of turbine

A component of a gas turbine engine is provided including at least one cooling hole formed in the component. The cooling hole has an interior surface that defines a flow path for air configured to cool a portion of the component.
United Technologies Corporation

Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir

A process for testing a turbine of a gas turbine engine at high altitudes, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.. .

Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir

A process for testing a combustor of a gas turbine engine, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the combustor to produce a decreased pressure such that a low atmospheric condition at the combustor exit is simulated.. .

Expansion seal

A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess.
United Technologies Corporation

Blade disk arrangement for blade frequency tuning

A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil..
Pratt & Whitney Canada Corp.

Method and system for modulated turbine cooling

A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor.
General Electric Company

Gear system architecture for gas turbine engine

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system.
United Technologies Corporation

Gear system architecture for gas turbine engine

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system.
United Technologies Corporation

Fire seal for use with a gas turbine engine

A fire seal for use with a gas turbine engine is provided. The fire seal includes a body comprising a first metallic sheet and a second metallic sheet adjacent thereto, each sheet having a plurality of segmented fingers, the segmented fingers of the first metallic sheet and the second metallic sheet overlapped such that the space between fingers on one sheet does not overlap the space between the fingers on the other sheet, at least one finger of the first sheet having at least one first flow aperture therein and at least one finger of the second sheet having at least one second flow aperture, the flow aperture of one sheet overlapping the flow aperture of the other sheet.
Rohr, Inc.

Integral oil tank heat exchanger

The present innovation relates to a gas turbine engine comprising an engine core with a combustion section, a fuel circuit fluidly coupled to the combustion section, an oil circuit fluidly coupled to the engine core, and an oil heat exchanger comprising a portion of the fuel circuit forming part of the oil circuit.. .
Unison Industries, Llc

Gear system architecture for gas turbine engine

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system.
United Technologies Corporation

Gas turbine engine

There is disclosed a gas turbine engine comprising a bypass duct defined between a radially inner wall and a radially outer wall. A support radially extends across the bypass duct.
Rolls-royce Plc

Shrouded blade for a gas turbine engine

A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face.
Pratt & Whitney Canada Corp.



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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