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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


High durability turbine exhaust case

Gkn Aerospace Sweden Ab

High durability turbine exhaust case

Fan blades with abrasive tips

United Technologies

Fan blades with abrasive tips

Fan blades with abrasive tips

Rolls-royce Plc

Method of inspecting the fan track liner of a gas turbine engine


Date/App# patent app List of recent Gas Turbine Engine-related patents
07/23/15
20150204439 
 Variable vane actuating system patent thumbnailnew patent Variable vane actuating system
A variable vane assembly for a gas turbine engine having an actuating system including a rotatable face gear and a respective pinion engaged to and extending transversely from the end of each of the moveable vanes. The teeth of each pinion define land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith.
Pratt & Whitney Canada Corp.


07/23/15
20150204347 
 Fan blades with abrasive tips patent thumbnailnew patent Fan blades with abrasive tips
A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing edge, a convex side, a concave side and a distal tip.
United Technologies Corporation


07/23/15
20150204245 
 Turbine blade platform seal assembly validation patent thumbnailnew patent Turbine blade platform seal assembly validation
A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab.
Solar Turbines Incorporated


07/23/15
20150204244 
 Selectively deoxygenated stored fuel system patent thumbnailnew patent Selectively deoxygenated stored fuel system
A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage..
United Technologies Corporation


07/23/15
20150204243 
 Structural support bracket for gas flow path patent thumbnailnew patent Structural support bracket for gas flow path
A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (ieps) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an iep and an inner support structure on the engine.
Siemens Energy, Inc.


07/23/15
20150204238 
 Low noise turbine for geared turbofan engine patent thumbnailnew patent Low noise turbine for geared turbofan engine
A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 hz.
Mtu Aero Engines Ag


07/23/15
20150204212 
 High durability turbine exhaust case patent thumbnailnew patent High durability turbine exhaust case
A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub.
Gkn Aerospace Sweden Ab


07/23/15
20150204210 
 Method of inspecting the fan track liner of a gas turbine engine patent thumbnailnew patent Method of inspecting the fan track liner of a gas turbine engine
A method of inspecting the fan track liner of a gas turbine engine of a type having a rotatable propulsive fan circumscribed by a fan track liner and having a plurality of fan blades extending radially outwardly from a central hub. The method comprises the steps of: affixing at least part of an inspecting device to the fan so as to be directed towards the fan track liner; and rotating the fan within the fan track liner to move said at least part of the inspecting device circumferentially relative to at least a region of the fan track liner to thereby scan said region of the fan track liner with said at least part of the inspecting device..
Rolls-royce Plc


07/23/15
20150204201 
 Contoured flowpath surface patent thumbnailnew patent Contoured flowpath surface
A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge.
United Technologies Corporation


07/23/15
20150203209 
 Gas turbine engine configuration interface patent thumbnailnew patent Gas turbine engine configuration interface
A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes.
Rolls-royce North American Technologies, Inc.


07/23/15
20150202707 
new patent

Attachment of structures having different physical characteristics


Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines.
United Technologies Corporation


07/23/15
20150202702 
new patent

Gas turbine engine cast structure finishing


A method of finishing a cast structure includes providing a cast exterior surface with an undesired cast feature and electrochemically machining the undesired cast feature to provide a finished contour.. .
United Technologies Corporation


07/16/15
20150198333 

Fuel injector with a diffusing main gas passage


A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage.
Solar Turbines Incorporated


07/16/15
20150198116 

Variable area exhaust mixer for a gas turbine engine


A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors.
United Technologies Corporation


07/16/15
20150198097 

Systems and methods for managing a combustor


Certain embodiments herein relate to systems and methods for managing a combustor of a gas turbine engine. In one embodiment, a system can include at least one memory configured to store computer-executable instructions and at least one controller configured to access the at least one memory and execute the computer-executable instructions.
General Electric Company


07/16/15
20150198092 

Dual function air diverter and variable area fan nozzle


A modulating fan air diverter and annular air-oil cooler for a gas turbine engine located in the inner fixed structure adjacent to the core cowl is provided. The fan air diverter modulates between an open position, corresponding to maximum fan nozzle area and airflow through the air-oil cooler, and a closed position, corresponding to minimum fan nozzle area and airflow through the air-oil cooler.
United Technologies Corporation


07/16/15
20150198091 

Electric probe assembly, gas turbine engine having same and cooling same


A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body.
Pratt & Whitney Canada Corp.


07/16/15
20150198062 

Turbine components with bi-material adaptive cooling pathways


The present application thus provides a turbine component for use in a hot gas path of a gas turbine engine. The turbine component may include an outer surface, an internal cooling circuit, an adaptive cooling pathway in communication with the internal cooling circuit and extending through the outer surface, and a cooling plug having two or more materials positioned within the adaptive cooling pathway..
General Electric Company


07/16/15
20150198059 

Gas turbine manual cleaning and passivation


A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine..
General Electric Company


07/16/15
20150198056 

Abradable seal having nanolayer material


A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon.
United Technologies Corporation


07/16/15
20150198053 

Gas turbine engine with exit flow discourager


A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between.
Solar Turbines Incorporated


07/16/15
20150198050 

Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine


An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and creating nearwall leading edge, pressure side and suction side nearwall cooling channels. The corrugated insert may be formed from a wall that oscillates in a repeating pattern between peaks and valleys, such that the peaks are closer to an inner surface of the outer wall forming the generally elongated hollow airfoil the corrugated insert may work in concert with the rows of partition walls to create periodic impingement on the inner surface of the outer wall such cooling system provides adequate cooling for use in environments in which few, if any, cooling holes are desired, such as in crude oil engine applications.
Siemens Energy, Inc.


07/16/15
20150198047 

Mistuned airfoil assemblies


A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub.
United Technologies Corporation


07/16/15
20150197456 

Protective coating systems for gas turbine engine applications and methods for fabricating the same


Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material.
Honeywell International Inc.


07/09/15
20150192912 

Method and system for combustion mode transfer for a gas turbine engine


A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine.
General Electric Company


07/09/15
20150192300 

Light weight swirler for gas turbine engine combustor and a manufacturing


A swirler body for a combustor of a gas turbine engine includes an annular mount face which defines at least one pocket and a method of manufacturing.. .
United Technologies Corporation


07/09/15
20150192299 

Compensating for thermal expansion via controlled tube buckling


One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel.
Delavan Inc.


07/09/15
20150192298 

Gas turbine engine with improved fuel efficiency


A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4.
United Technologies Corporation


07/09/15
20150192165 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation


07/09/15
20150192072 

Fluid transport system having divided transport tube


A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages..
United Technologies Corporation


07/09/15
20150192071 

Geared turbofan gas turbine engine architecture


A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor.
United Technologies Corporation


07/09/15
20150192070 

Geared turbofan gas turbine engine architecture


A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
United Technologies Corporation


07/09/15
20150192069 

Recuperator for gas turbine engine


A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core.
Pratt & Whitney Canada Corp.


07/09/15
20150192039 

Auxillary steam generation arrangement for a combined cycle power plant


A combined cycle plant (10) including: a gas turbine engine (12) having a compressor (14), a combustor and a gas turbine (16); a heat recovery steam generator (20) (hrsg) configured to receive exhaust from the gas turbine engine; a steam turbine (22, 24) configured to receive steam from the hrsg; a supplemental air arrangement (40) configured to generate supplemental heated air (42) when operating and to operate independent of the gas turbine engine; and a kettle boiler (26, 28) configured to use heat from the supplemental heated air to generate steam used in the steam turbine. .

07/09/15
20150192038 

Combined cycle plant injection water preheating arrangement


A combined cycle plant (10), including a heat recovery steam generator (hrsg) (36), a working fluid which is heated by the hrsg and effective to operate a steam turbine (38), and a blowdown heat transfer arrangement (90, 92, 94,102, 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to injection water (28), a gas turbine engine (16) having a compressor (18), a combustor (20), and a turbine (22), and a water injection arrangement (30) configured to inject the injection water into the combustor. .

07/09/15
20150192037 

Combined cycle plant fuel preheating arrangement


A combined cycle plant (10), including: a gas turbine engine (16) having a compressor (18), a combustor (20), and a gas turbine (22); and a heat recovery steam generator (hrsg) (36), a steam turbine (38), working fluid heated by the hrsg and effective to turn the steam turbine, and a blowdown heat transfer arrangement (90, 92, 94, 102, and 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to fuel (24) used in the combustor.. .

07/09/15
20150192036 

Preheating arrangement for a combined cycle plant


A power generation station (10), including: a combined cycle plant (12) having a gas turbine engine (20); a hrsg (30) configured to receive engine exhaust from the gas turbine engine and to generate steam, and a steam turbine (38, 40) configured to use the steam to develop mechanical energy; an auxiliary boiler (14) configured to generate heat used to create auxiliary steam for use in the combined cycle plant and to generate auxiliary boiler exhaust (52); and an auxiliary boiler exhaust heat transfer arrangement (16) configured to transfer heat present in the auxiliary boiler exhaust to the combined cycle plant.. .

07/09/15
20150192034 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation


07/09/15
20150191252 

System and coordinated control of a power system


An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (lp) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (hp) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.. .
Rolls-royce North American Technologies, Inc.


07/02/15
20150185111 

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..
Rolls-royce North American Technologies, Inc.


07/02/15
20150185089 

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.
Siemens Energy, Inc.


07/02/15
20150184858 

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


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.
United Technologies Corporation


07/02/15
20150184611 

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


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.
General Electric Company


07/02/15
20150184535 

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.
Rolls-royce North American Technologies, Inc.


07/02/15
20150184530 

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.
General Electric Company


07/02/15
20150184528 

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.
General Electric Company


07/02/15
20150184516 

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.
Solar Turbines Incorporated


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




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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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