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Gas Turbine Engine patents



      
           
This page is updated frequently with new Gas Turbine Engine-related patent applications. Subscribe to the Gas Turbine Engine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine Engine RSS RSS


Control system and method for controlling a gas turbine engine during transients

Control system and method for controlling a gas turbine engine during transients

System for sealing between combustors and turbine of gas turbine engine

System for sealing between combustors and turbine of gas turbine engine

Date/App# patent app List of recent Gas Turbine Engine-related patents
07/02/15
20150185111
 System and  optimizing component life in a power system patent thumbnailnew patent System and optimizing component life in a power system
An aircraft includes first and second gas turbine engines having a first component and a second component that is redundant with the first component, and an engine health monitoring system (ehms) coupled to the first and second gas turbine engines. The ehms is configured to calculate a remaining useful life (rul) of the first component and of the second component, calculate a rate-of-life consumption of the first component and of the second component, predict when failure of the first component and failure of the second component will occur based on the rul of each and based on the respective rate-of-life consumption of each, and provide instructions for altering operation of the aircraft that affects the rul of the first or second component..
07/02/15
20150185089
 Acoustic transducer in system for gas temperature measurement in gas turbine engine patent thumbnailnew patent Acoustic transducer in system for gas temperature measurement in gas turbine engine
An apparatus for controlling operation of a gas turbine engine including at least one acoustic transmitter/receiver device located on a flow path boundary structure. The acoustic transmitter/receiver device includes an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends, an acoustic sound source located at the first end, and an acoustic receiver located within the sound passage between the first and second ends.
07/02/15
20150184858
 Method of operating a multi-stage flamesheet combustor patent thumbnailnew patent Method of operating a multi-stage flamesheet combustor
The present invention discloses a novel way of controlling a gas turbine engine to reduce emissions levels when demand for power from the gas turbine engine is reduced. The operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide are kept within acceptable levels..
07/02/15
20150184857
 Microcircuit cooling for gas turbine engine combustor patent thumbnailnew patent Microcircuit cooling for gas turbine engine combustor
A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel.
07/02/15
20150184611
 Control  controlling a gas turbine engine during transients patent thumbnailnew patent Control controlling a gas turbine engine during transients
A control system and method for a gas turbine engine are provided a controller (40) is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature sensor (42).
07/02/15
20150184594
 Systems and methods to maintain stability of fuel flow in gas turbine engines patent thumbnailnew patent Systems and methods to maintain stability of fuel flow in gas turbine engines
A system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas turbine.
07/02/15
20150184535
 Active synchronizing ring patent thumbnailnew patent Active synchronizing ring
An improved system, apparatus and method for controlling vane angles in a gas turbine engine, and more specifically, for correcting vane angle error in a gas turbine engine. An active synchronization ring comprises a plurality of micro-actuators coupled to the synchronization ring to correct distortion in the synchronization ring.
07/02/15
20150184530
 Turbine nozzle and  cooling a turbine nozzle of a gas turbine engine patent thumbnailnew patent Turbine nozzle and cooling a turbine nozzle of a gas turbine engine
The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane.
07/02/15
20150184528
 System for sealing between combustors and turbine of gas turbine engine patent thumbnailnew patent System for sealing between combustors and turbine of gas turbine engine
A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors.
07/02/15
20150184516
 Nozzle endwall film cooling with airfoil cooling holes patent thumbnailnew patent Nozzle endwall film cooling with airfoil cooling holes
A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall, and an airfoil extending between the upper endwall and the lower endwall.
06/25/15
20150180309

Dual redundant motor/ generator for an engine


An exemplary electrical system may include a power plant and a dual motor/generator assembly coupled to each other. The power plant may be a gas turbine engine, and may be operable to provide motive power.
Rolls-royce Corporation
06/25/15
20150177091

Devices and methods for balancing a high-pressure spool of a gas turbine engine


Devices and methods useful for balancing high-pressure spools of gas turbine engines are disclosed. An exemplary device may comprise: an input shaft configured to be coupled to an output of an accessory gear box driven by a high-pressure spool of a gas turbine engine; a first trigger rotatably coupled to the input shaft at a first speed ratio; and a sensor configured to detect the trigger at each revolution of the trigger.
Pratt & Whitney Canada Corp.
06/25/15
20150176590

Flow outlet


A noise attenuation panel for a bleed flow is presented that causes a total pressure loss of the bleed flow before it is exhausted. The total pressure loss results from at least two regions in which the flow area contracts and then rapidly expands, with the rapid expansion causing mixing and turbulence rather than full total pressure recovery.
Rolls-royce Plc
06/25/15
20150176530

Ultra high overall pessure ratio gas turbine engine


A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor rotors, with an upstream one of the compressor rotors are connected to rotate on a shaft with a fan drive turbine and a reduced speed fan rotor through a gear reduction.
United Technologies Corporation
06/25/15
20150176502

Method of controlling a gas turbine engine using real-time component temperature data


A device and methods are provided for controlling a gas turbine engine based at least in part on real-time detection of spatially resolved temperature distributions of a turbine engine components. In one embodiment, a method includes detecting surface temperature of one or more blade elements, by an thermal probe, in a plurality of radial locations of an airfoil row to determine real-time spatially resolved surface temperature data for the one or more blade elements of the airfoil row, and controlling the engine based on the real-time spatially resolved surface temperature data..
United Technologies Corporation
06/25/15
20150176497

Geared turbofan with a gearbox upstream of a fan drive turbine


A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. An output of the speed change mechanism connects to the fan..
United Technologies Corporation
06/25/15
20150176495

Fluid manifold for gas turbine engine and delivering fuel to a combustor using same


The described gas turbine engine fuel manifold includes one or more fuel conduits defined within a ring-shaped manifold body, each of the fuel conduits being fluidly connected to a respective separate group of fuel injection nozzles. Each of the fuel conduits, which extend from a conduit inlet to a conduit end, include a first portion extending continuously between the conduit inlet and an inflexion of the conduit, and a second portion downstream of the first portion and connected thereto in serial flow communication, the second portion extending between the inflexion and the conduit end.
Pratt & Whitney Canada Crop.
06/25/15
20150176494

Supporting structure for a gas turbine engine


A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, an inlet side for primary gas flow entrance, and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge, wherein a locus of points midway between the two opposite sides forms a mean camber line of each radial element, wherein at least one of the radial elements comprises a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure, and wherein the gas passage arrangement comprises a radially extending gas channel arranged inside the radial element and at least one opening in communication with said gas channel, wherein the at least one opening is arranged at one of the two opposite sides of the radial element.. .
Gkn Aerospace Sweden Ab
06/25/15
20150176493

Gas turbine engine forward bearing compartment architecture


A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure..
United Technologies Corporation
06/25/15
20150176492

Oil tank and scavenge pipe assembly of a gas turbine engine and delivering an oil and air mixture to same


An oil tank and scavenge pipe assembly of a gas turbine engine comprises a tank, and a scavenge pipe having a discharge portion disposed inside the tank. The discharge portion comprises a first portion having first and second ends.
Pratt & Whitney Canada Corp.
06/25/15
20150176486

Gas turbine engine with transmission


A gas turbine engine with a transmission having a variable ratio is discussed. A first gear train is in driving engagement with the low pressure spool and has a first output gear.
Pratt & Whitney Canada Corp.
06/25/15
20150176484

Geared turbofan with a gearbox aft of a fan drive turbine


A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan..
United Technologies Corporation
06/25/15
20150176432

Gas turbine case and reinforcement strut for same


A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components.
Pratt & Whitney Canada Corp.
06/25/15
20150176425

Wall construction for gaspath traversing component


A gaspath traversing component of a gas turbine engine comprises a wall having an outer edge surface and a thickness relative to the gaspath, the wall having a plurality of layers of composite materials forming the thickness. A wear indication layer is embedded within the plurality of layers of composite material, the wear indication layer being visually contrasting with the composite material.
Pratt & Whitney Canada Corp.
06/25/15
20150176420

Supporting structure for a gas turbine engine


A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element. .
06/25/15
20150176418

Compressor variable vane assembly


A variable vane assembly for a gas turbine engine compressor with a plurality of pivoting variable vanes extending between inner and outer shrouds and having an overhang portion that protrudes from a button at opposed ends of the vane. A plurality of projections, disposed on at least one of the inner and outer shrouds, protrude into the gas path relative to a nominal gas path boundary of the shrouds.
Pratt & Whitney Canada Corp.
06/25/15
20150176414

Internal turbine component electroplating


Method and apparatus are provided for electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine component.. .
Howmet Corporation
06/25/15
20150176412

Rotor blade and guide vane airfoil for a gas turbine engine


The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage.
Alstom Technology Ltd
06/25/15
20150174707

Plural layer putty-powder/slurry application superalloy component crack vacuum furnace healing


A process for repairing combined heavy erosion and thermal fatigue cracks and/or other defects, such as large cracks, in a high temperature superalloy component, such as a vane in a turbine section of a gas turbine engine, that does not require mechanical grinding to prepare the defect site. The process includes depositing a loose finely granulated superalloy powder or a low viscosity superalloy slurry in the crack up to a suitable level and then depositing a superalloy putty layer on the superalloy powder or slurry at the top of the crack a braze putty layer is then deposited over the superalloy putty layer and the component is sintered in a vacuum furnace to harden the superalloy putty and powder or slurry to repair the defect..
06/18/15
20150172566

Natural resolution processing for lwir images


A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (lwir) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of lwir images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel.
United Technologies Corporation
06/18/15
20150172565

Composite image processing for lwir images using geometric features


A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes.
United Technologies Corporation
06/18/15
20150168262

Single crystal turbine blade lifing process and system


A system and methods for lifing a single crystal turbine blade of a gas turbine engine is disclosed. The system and methods determine the anisotropic strain of the single crystal turbine blade caused by fatigue and creep by resolving the shear stresses on each of the primary slip systems of the single crystal turbine blade.
Solar Turbines Incorporated
06/18/15
20150168139

Method and determining gas turbine dampening cone inner diameter


gas turbine engine generally ring-shaped dampening cone inner diameters, including those having spherical or other convex inner diameter surface profiles, are determined with a fixture including a displacement indicator having an axis of displacement in alignment with a locating pin. The dampening cone inner diameter surface is placed in contact with the locating pin on one side and a displacement point on the other side, so that the dampening cone inner diameter surface circumscribes a contact surface formed on the locating pin and the displacement point.
06/18/15
20150167986

Swirling midframe flow for gas turbine engine having advanced transitions


A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.. .
06/18/15
20150167985

Gas turbine engine fuel air mixer


A gas turbine engine device is disclosed for mixing fuel and air prior to a combustion. The device includes a pilot mixer and a main mixer each having a fuel opening for the delivery of fuel to one or more passages.
Rolls-royce Corporation
06/18/15
20150167980

Axial stage injection dual frequency resonator for a combustor of a gas turbine engine


A gas turbine engine (202) including a secondary fuel stage (218) which also functions as a dual frequency resonator. The engine includes a combustor (210) and a casing (205) enclosing the combustor to define a volume (214).
06/18/15
20150167979

First stage nozzle or transition nozzle configured to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine


The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine. For example, in one embodiment, a gas turbine engine may include a combustor having a combustion flow.
General Electric Company
06/18/15
20150167693

Gas turbine device


A gas turbine device in which the low frequency vibrations or the low frequency noises during the low load operation can be effectively suppressed with no increase of the pressure loss of the exhaust gas being triggered includes a gas turbine engine provided with an exhaust diffuser forming an upstream portion of an exhaust gas passage, an exhaust strut provided in the diffuser (20), and a swirling flow blocking plate. The swirling flow blocking plate is disposed on a downstream side of the exhaust strut in the exhaust gas passage so as to extend in an axial direction..
Kawasaki Jukogyo Kabushiki Kaisha
06/18/15
20150167676

Gas turbine engine for long range aircraft


A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors.
United Technologies Corporation
06/18/15
20150167557

Seal for gas turbine engines


A gas turbine engine assembly includes a support component, an engine component, and a seal. The annular support component is formed to include a notch.
Rolls-royce North American Technologies, Inc.
06/18/15
20150167498

Joint between components


A joint assembly between a first gas turbine engine casing and a second gas turbine casing, the first gas turbine engine casing having a plurality of circumferentially spaced attachment points and the second gas turbine casing having a plurality of circumferentially spaced attachment points for securing the first gas turbine casing and the second gas turbine casing together, wherein each attachment point on the first gas turbine casing is circumferentially offset from a respective attachment point on the second gas turbine casing, and connected by a flexure member that permits limited relative movement of the attachment point on the first gas turbine engine casing and its respective attachment point on the second gas turbine casing.. .
Rolls-royce Deutschland Ltd & Co Kg
06/18/15
20150167493

Turbine bucket and cooling a turbine bucket of a gas turbine engine


The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially outward from the platform, and a number of cooling passages defined at least partially within the airfoil.
General Electric Company
06/18/15
20150167491

Gas turbine engine comprising a composite component and a metal component which are connected by a flexible fixing device


A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.. .
Snecma
06/18/15
20150167488

Adjustable clearance control system for airfoil tip in gas turbine engine


An airfoil system for use in a gas turbine engine having an adjustable clearance control system including an axially adjustable ring segment releasably coupled to the stationary turbine component whereby the axially adjustable ring segment may be controlled independently of other airfoil stages is disclosed the adjustable clearance control system may thus control the flow of hot gases passing one particular airfoil stage while the flow passing other airfoil stages within the component of the turbine engine remains unchanged the adjustable clearance control system may control the size of the gap between the axially adjustable ring segment and the tip of an airfoil through axial movement of the axially adjustable ring segment. The axially adjustable ring segment may include a radially inward contact surface that is positioned nonparallel and nonorthogonal relative to a direction of movement of the axial adjustable ring segment..
06/18/15
20150167480

Methods and sealing a gas turbine engine rotor assembly


A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces.
General Electric Company
06/18/15
20150167475

Airfoil of gas turbine engine


An airfoil of gas turbine engine is provided, which can improve cooling efficiency at a leading edge of the airfoil even when a location of combustion gas stagnation changes, without having to increase cooling air flowrate. The airfoil of gas turbine engine includes a cooling passage formed inside the airfoil to guide cooling air, and one or more cooling slots in elongated form, extending through the leading edge of the airfoil to a direction of the cooling passage and across a lengthwise direction of the leading edge..
Korea Aerospace Research Institute
06/18/15
20150166193

Gas turbine cowl


A gas turbine engine (30) comprising a rear cowl (38) defining an exhaust aperture (40) and a motive system. The rear cowl (38) comprises at least one panel (42) and the motive system is operable to selectively move the panel (42) between deployed and stowed configurations by rotation of the panel (42) about an axis substantially parallel to the main rotational axis of the engine (30).
Rolls-royce Plc
06/11/15
20150159878

Combustion system for a gas turbine engine


A combustor for a gas turbine engine includes a pilot fuel injector and a plurality of circumferentially located main injectors for injecting fuel and air into a combustion chamber defined by a liner wall of a combustor basket. A combustion zone is located in the combustion chamber where the fuel and air are ignited to produce hot combustion gases.
06/11/15
20150159877

Late lean injection manifold mixing system


A manifold mixing system for combustor of a gas turbine engine includes a fuel supply, a fuel injector coupled with the fuel supply, and a manifold mixer cooperable with the fuel injector and including mixing air inlets. The fuel injector is displaceable relative to the manifold mixer while being positioned to deliver fuel from the fuel supply to the manifold mixer.
General Electric Company
06/11/15
20150159871

Gas turbine engine wall


A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein.
General Electric Company
06/11/15
20150159563

Automated extended turndown of a gas turbine engine combined with incremental tuning to maintain emissions and dynamics


An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a gt engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions.
06/11/15
20150159559

Method and system for compressor on line water washing with anticorrosive solution


Methods and systems may dispense turbine engine anticorrosive protection. In an embodiment, a method may include determining a condition of a gas turbine engine while the gas turbine engine is online, wherein the condition includes the power output level of the gas turbine engine and applying, based on the condition, an anticorrosion fluid to the gas turbine engine while the gas turbine engine is online..
General Electric Company
06/11/15
20150159558

Method and system for dispensing gas turbine anticorrosion fluid


Disclosed herein are methods and systems for dispensing turbine engine anticorrosive protection. In an embodiment, a method may include selecting an anticorrosion fluid for a gas turbine engine and applying the anticorrosion fluid to the gas turbine engine..
General Electric Company
06/11/15
20150159557

Gas turbine engine imparting corrosion resistance to gas turbine engines


Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction piping and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods.
General Electric Company
06/11/15
20150159556

Gas turbine engine imparting corrosion resistance to gas turbine engines


Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods.
General Electric Company
06/11/15
20150159555

Internal heating using turbine air supply


A gas turbine engine that includes a heat exchanger for heating a fuel gas using compressed air generated by the engine. The heat exchanger is positioned within an outer housing of the engine and receives the fuel gas at a first input prior to the fuel being mixed with a combustion portion of the compressed air and receives a cooling portion of the compressed air at a second input prior to the cooling portion of the compressed gas being sent to cooling flow channels.
06/11/15
20150159500

System and turbine blade clearance control


A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust.
Honeywell International Inc.
06/11/15
20150159499

Control of a gas turbine engine


A thrust demand signal is provided to a processor of a gas turbine engine and is modified, according to growth time constants of a rotor and/or a casing of the engine, in order to control the rotational speed or the rate of change of rotational speed of the engine so as to prevent contact between the rotor and the casing.. .
Rolls-royce Plc
06/11/15
20150159492

Self-healing environmental barrier coating


The present inventions incorporate self-healing mechanisms into current and future ebc systems. Such approaches have the potential to form environmental protection materials (i.e.
Directed Vapor Technologies International, Inc.
06/11/15
20150159490

Internally cooled airfoil for a rotary machine


The invention refers to an internally cooled casted airfoil for a rotary machine, preferably a gas turbine engine comprising a suction and a pressure side wall each extending in an axial direction, i.e. From a leading to a trailing edge region of said airfoil.
Alstom Technology Ltd
06/11/15
20150159489

Cooling configuration for a gas turbine engine airfoil


A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber.
Siemens Aktiengesellschaft
06/04/15
20150152789

Multi-bypass stream gas turbine engine with enlarged bypass flow area


A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within the engine, radially exterior to the first bypass flow path housing. An axially downstream portion of the first bypass flow path housing includes a stepwise increase in area compared with an axially adjacent upstream portion of the first bypass flow path housing, thereby defining a component placement cavity in the axially downstream portion..
United Technologies Corporation
06/04/15
20150152788

Gas turbine engine comprising an exhaust cone attached to the exhaust casing


An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.. .
Snecma
06/04/15
20150152787

Low noise compressor rotor for geared turbofan engine


A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor.
United Technologies Corporation
06/04/15
20150152786

Drain pipe arrangement and gas turbine engine comprising a drain pipe arrangement


A pipe arrangement for a turbomachine is provided having a fluid pipe for guiding fluids and a coupling element for coupling the fluid pipe to a temperature affected component. The coupling element is configured to provide a first connection between the coupling element and the component by a first end of the coupling element.
Siemens Aktiengesellschaft
06/04/15
20150152746

Slotted distribution sleeve for a seal plate


A seal assembly for a gas turbine engine, may be manufactured in two pieces, the first piece is a seal plate with a cavity around its inner wall and the second piece is a sleeve that mounts in the cavity of the seal plate. The sleeve may have oil distribution channels that deliver oil to subsequent components and apertures that deliver oil to the seal plate.
United Technologies Corporation
06/04/15
20150152738

Turbine airfoil cooling passage with diamond turbulator


A turbulator having a diamond-shaped configuration where a front portion of the turbulator is a mirror image of a rear portion of the turbulator, and where the turbulator has application for cooling flow channels in a blade of a gas turbine engine. An array of the diamond-shaped turbulators is positioned in rows relative to the flow of the cooling air so that a turbulator in one of the rows is positioned relative to the gap between two turbulators in an adjacent row to break up the flow of air flowing between the turbulators..
06/04/15
20150152736

Turbine endwall with micro-circuit cooling


A micro-circuit cooling module for providing endwall cooling for a vane assembly in a gas turbine engine. The micro-circuit cooling module includes an outer perimeter rail, an upper plate and a lower plate defining a mixing chamber therein.
06/04/15
20150152734

Turbine airfoil with local wall thickness control


A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.. .
General Electric Company
05/28/15
20150147479

Methods for the formation of cooling channels, and related articles of manufacture


A method for the formation of channels on a metallic substrate is described. The method includes the steps of applying at least one layer of a metallic coating material onto a surface of the substrate by a cold spray technique, so as to define boundary walls for the channels, and to build the boundary walls to a desired height.
General Electric Company
05/28/15
20150147182

Adjusted rotating airfoil


A compressor component having an airfoil with a profile in accordance with table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length.
05/28/15
20150147165

Methods for the formation and shaping of cooling channels, and related articles of manufacture


A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough.
General Electric Company
05/28/15
20150147156

Gas turbine engine


A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element.
Rolls-royce Plc


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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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