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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


Date/App# patent app List of recent Gas Turbine Engine-related patents
02/26/15
20150056073
 Method and system for cooling rotor blade angelwings patent thumbnailnew patent Method and system for cooling rotor blade angelwings
A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity.
General Electric Company
02/26/15
20150053750
 High temperature brazing fixture and  manufacture patent thumbnailnew patent High temperature brazing fixture and manufacture
A high temperature brazing fixture and method of manufacture for a gas turbine component made of a superalloy is disclosed herein. The high temperature brazing fixture includes a first and second frame member, a support member, and positioning member, all of which are made from the superalloy and fastened together using tab and tab lock couplings.
Solar Turbines Incorporated
02/26/15
20150052910
 Apparatus and  servicing gas turbine engines patent thumbnailnew patent Apparatus and servicing gas turbine engines
The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure.
General Electric Company
02/26/15
20150052908
 Bleed duct assembly for a gas turbine engine patent thumbnailnew patent Bleed duct assembly for a gas turbine engine
A bypass duct has a support unit comprising a pair of aerofoils arranged as an “a” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus.
Rolls-royce Deutschland Ltd & Co Kg
02/26/15
20150052907
 Thermal management system for gas turbine engine patent thumbnailnew patent Thermal management system for gas turbine engine
A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an environmental control system (ecs) pre-cooler or an air oil cooler (aoc) “peaker” through a common inlet.. .
United Technologies Corporation
02/26/15
20150052899
 Airblast fuel injector patent thumbnailnew patent Airblast fuel injector
An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile.
Rolls-royce Plc
02/26/15
20150052872
 Thermal isolating service tubes and assemblies thereof for gas turbine engines patent thumbnailnew patent Thermal isolating service tubes and assemblies thereof for gas turbine engines
Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member.
Honeywell International Inc.
02/26/15
20150052749
 Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority patent thumbnailnew patent Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority
A method of fabricating an integrally bladed rotor for gas turbine engines according to one aspect includes a step of positioning a blade on a hub in a joining procedure by using a priority surface of the blade as a reference surface. The priority surface is determined in relation to importance of surface functionality of the blades during engine operation.
Pratt & Whitney Canada Corp.
02/19/15
20150050158
 Gas turbine engine component including a compliant layer patent thumbnailGas turbine engine component including a compliant layer
A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel..
Rolls-royce North American Technologies, Inc.
02/19/15
20150050151
 Annulus filler patent thumbnailAnnulus filler
An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, the annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc.
Rolls-royce Plc
02/19/15
20150050150

Annulus filler


An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc.
Rolls-royce Plc
02/19/15
20150050127

Air with integral spring for a gas turbine engine exhaust drive


A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.. .
United Technologies Corporation
02/19/15
20150050123

Switched reluctance, fully superconducting, integrated ring turbine motor, generator gas turbine, engine stage (ssrgts)


A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring.
02/19/15
20150047361

Nozzle with multi-tube fuel passageway for gas turbine engines


A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip.
Siemens Aktiengesellschaft
02/19/15
20150047359

Axial flow machine cooling system


This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.. .
Rolls-royce Plc
02/19/15
20150047315

Gas turbine engine flow duct having integrated heat exchanger


A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.. .
Rolls-royce North American Technologies, Inc.
02/12/15
20150046126

Gas turbine engine rotor assembly optimization


A method for optimizing a rotor assembly for a gas turbine engine is disclosed. The rotor assembly includes rotating parts including a first journal and one or more rotor disks.
Solar Turbines Incorporated
02/12/15
20150044056

Airfoil with leading edge reinforcement


A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg.
Rolls-royce Corporation
02/12/15
20150044054

Composite retention feature


A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post.
Rolls-royce Corporation
02/12/15
20150044050

Composite blade with an integral blade tip shroud and forming the same


A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed..
Rolls-royce Corporation
02/12/15
20150044049

Dovetail retention system for blade tracks


A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts.
Rolls-royce Corporation
02/12/15
20150044044

Turbine shroud


A turbine shroud for a gas turbine engine includes an annular metallic carrier, a ceramic blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier.
Rolls-royce Corporation
02/12/15
20150044035

High porosity abradable coating


An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters.
Solar Turbines Incorporated
02/12/15
20150044029

Aerofoil


An aerofoil component of a gas turbine engine has an aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion has a pressure side outer wall and a suction side outer wall, each extending from the leading edge to the trailing edge of the aerofoil portion.
Rolls-royce Plc
02/12/15
20150044028

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size


According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension d that is based on a dimension of the fan blades.
United Technologies Corporation
02/12/15
20150042023

Hybrid part made from monolithic ceramic skin and cmc core


A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material.
United Technologies Corporation
02/12/15
20150041274

Clutch coupled to gas turbine engine and cooling


A gas turbine engine clutch includes a dry clutch assembly, forward and aft working areas, and a shaft. The dry clutch assembly is operative to receive power from a gas turbine engine.
Rolls-royce Corporation
02/12/15
20150040577

System and preventing ice crystal accretion in gas turbine engines


A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.. .
Honeywell International Inc.
02/12/15
20150040575

Fuel igniter assembly having heat-dissipating element and methods of using same


A combustor for a gas turbine engine includes a combustion chamber and a fuel igniter assembly. The combustion chamber is defined by an annular inner combustor liner and an annular outer combustor liner.
Unison Industries, Llc
02/12/15
20150040572

Gas turbine engine combustor with fluidic control of swirlers


A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly.
Honeywell International Inc.
02/12/15
20150040570

Gas turbine engine component having foam core and composite skin with cooling slot


In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component.
Rolls-royce North American Technologies, Inc.
02/12/15
20150040538

Rotor noise suppression


An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture..
Rolls-royce Corporation
02/12/15
20150040393

Manufacturing exhaust diffuser shell with strut shield collar and joint flange


Manufacture of a gas turbine exhaust diffuser shell (40a/40b) to achieve a final cross-sectional shell geometry by forming an opening (76) in the shell to receive a strut shield collar (46); forming a compensating outward bowing (78) of the shell around the opening that departs from a desired final shell geometry in an amount and shape that compensates for a welding shrinkage when welding the collar in the opening; and welding the collar in the opening. This produces the desired shell geometry after the welding.
02/05/15
20150037145

Systems relating to axial positioning turbine casings and blade tip clearance in gas turbine engines


A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction.. .
General Electric Company
02/05/15
20150037133

System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines


A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means..
General Electric Company
02/05/15
20150036781

Health monitoring of igniters


Methods and associated devices useful for the health monitoring of igniters of gas turbine engines are disclosed. Exemplary embodiments disclosed include the use of an accumulated spark count to an igniter to obtain an indication of wear on the igniter and/or the remaining life of the igniter.
Pratt & Whitney Canada Corp.
02/05/15
20150033836

Methods and inspecting cooling holes


Methods and apparatus for inspecting cooling holes in a wall of a combustor of a gas turbine engine are disclosed. An exemplary method disclosed may comprise: heating the wall of the combustor; directing a flow of cooling fluid through the one or more cooling holes in the wall of the combustor while the wall is being heated; acquiring a first measurement indicative of a flow rate of the cooling fluid through the one or more cooling holes; and acquiring a second measurement indicative of a cooling effectiveness provided by the cooling fluid flowing through the one or more cooling holes at the flow rate..
Pratt & Whitney Canada Corp.
02/05/15
20150033759

Gas turbine engine component


The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein an annular load transfer structure (23) extends circumferentially along an inner side of the inner ring (20) and also inwards in a radial direction of the component (27). The first portion (23a), at least along a part of the circumference, is inclined in the radial direction in relation to a second portion (23b), wherein the two inclined portions (23a, 23b) are connected in a connection zone (26) between the inclined portions (23a, 23b), and wherein a radial and/or axial position of the connection zone (26) varies along the circumference such that the radial/axial position of the connection zone in a location that circumferentially corresponds to a first element (22a), i.e.
Gkn Aerospace Sweden Ab
02/05/15
20150033757

System and a gas turbine engine sensor


A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold..
Exxonmobil Upstream Research Company
02/05/15
20150033749

System and controlling combustion and emissions in gas turbine engine with exhaust gas recirculation


In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber.
Exxonmobil Upstream Research Company
02/05/15
20150033748

System and an oxidant heating system


A system includes an oxidant compressor and a gas turbine engine. The gas turbine engine includes a combustor section having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine.
Exxonmobil Upstream Research Company
02/05/15
20150033746

Heat shield with standoffs


A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs.
Solar Turbines Incorporated
02/05/15
20150033560

Aerofoil component handling tool


A handheld tool facilitates the removal of an aerofoil from an array of aerofoils for an axial flow machine includes a body portion, and first and second jaw members depending from the body portion. The first jaw member is shaped to be insertable between a first aerofoil and an adjacent aerofoil in the array so as to contact a first surface of the first aerofoil.
Rolls-royce Plc
01/29/15
20150030947

Solid oxide fuel cell system


A solid oxide fuel cell system (10) comprises a solid oxide fuel cell stack (12) and a gas turbine engine (14), a compressor (24) of the gas turbine engine (14) is arranged to supply oxidant to the cathodes (22) of the solid oxide fuel cell stack (12) and a fuel supply (32) is arranged to supply fuel to the anodes (20) of the solid oxide fuel cell stack (12). A portion of the unused oxidant from the cathodes (22) of the solid oxide fuel cell stack (12) is supplied back to the cathodes (22) of the solid oxide fuel cell stack (12).
Rolls-royce Fuel Cell Systems Limited
01/29/15
20150030443

Split damped outer shroud for gas turbine engine stator arrays


A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.. .
United Technologies Corporation
01/29/15
20150030432

Trailing edge cooling arrangement for an airfoil of a gas turbine engine


An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114′) defining plugged holes (115) and cooling holes (116) along a radial direction (117).
01/29/15
20150030428

Method for enhancing power of a gas turbine engine


A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module.
Solar Turbines Incorporated
01/29/15
20150028133

Enhanced mixing tube elements


The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel.
General Electric Company
01/29/15
20150027811

Maintenance assembly adaptable within gas turbine engine


The maintenance assembly, for workers to perform maintenance activities within a gas turbine engine, is capable of being arranged within a cavity, generally around a combustor, accessible from a manhole of the gas turbine engine. The maintenance assembly includes a platform, and an inflatable member cooperatively configured to the platform.
Alstom Technology Ltd
01/29/15
20150027211

Flame monitoring of a gas turbine combustor using a characteristic spectral pattern from a dynamic pressure sensor in the combustor


The state of a flame in a gas turbine engine combustor is acoustically monitored using a dynamic pressure sensor within the combustor. A spectral pattern of a dynamic pressure sensor output signal from the sensor is compared with a characteristic frequency pattern that includes information about an acoustic pattern of the flame and information about acoustic signal canceling due to reflections within the combustor.
Siemens Energy, Inc.
01/29/15
20150027210

Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine


An apparatus is provided for measuring a depth of a groove defined between adjacent steeples of a rotor of a turbine. The groove is adapted to receive a root of a blade.
01/29/15
20150027101

Geared gas turbine engine architecture for enhanced efficiency


An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees fahrenheit at take-off.
United Technologies Corporation
01/29/15
20150027100

System for performing staging control of a multi-stage combustor


A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds.
Rolls-royce Controls And Data Services Limited
01/22/15
20150023780

Liner attaching scheme


A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface.
United Technologies Corporation
01/22/15
20150023776

Fluid cooling arrangement for a gas turbine engine and method


A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path.
Hamilton Sundstrand Corporation
01/22/15
20150022655

Apparatus and method using a linear array of optical sensors for imaging a rotating component of a gas turbine engine


Apparatus and method using a linear array (22) of optical sensors (24) for imaging a rotating component (12) of a gas turbine engine. A viewing probe (16) may include the linear array of optical sensors disposed in the probe to acquire image data that may be made up of a series of line scans capturing views of the component passing within a field of view of the probe.
01/22/15
20150021860

Leaf seal


There is disclosed a leaf seal (131) for effecting a seal between first (134) and second 1) coaxial components arranged for relative rotation about a common axis. The seal is particularly suited for use in a gas turbine engine, and has: an annular pack (50) of stacked leaves (132) mountable to said first component (134) at root portions (140) of the leaves distal to the second component (51) and extending towards the second component (51) such that end edges(136) of the leaves (132) are proximal to the second component (51); and a plurality of seal elements (52) which cooperate to define an annulus extending around a surface (137) of the second component (51).
Rolls-royce Plc
01/22/15
20150020530

Gas turbine emissions control system and method


Embodiments of the present disclosure are directed towards a system including a gas turbine engine, a selective catalytic reduction system, and a control system configured to regulate operation of the selective catalytic reduction system based at least partially on preset variations in an emissions compound of exhaust gases produced by the gas turbine engine.. .
General Electric Company
01/22/15
20150020529

Gas turbine emissions control system and method


Embodiments of the present disclosure are directed towards a system including a gas turbine engine configured to produce exhaust gas, a selective catalytic reduction system configured to produce processed exhaust gas from the exhaust gas, and a control system. The control system includes a first controller configured to regulate operation of the selective catalytic reduction system, a second controller configured to regulate operation of the gas turbine engine, and an optimizer configured to coordinate operation of the first controller and the second controller to simultaneously maximize a first level of an emissions compound in the exhaust gas and regulate injection of a reductant into the selective catalytic reduction system to reduce a second level of the emissions compound in the processed exhaust gas to a first desired level of the emissions compound in the processed exhaust gas..
General Electric Company
01/22/15
20150020528

Fuel manifold and fuel injector arrangement for a combustion chamber


A fuel manifold and fuel injector arrangement for a gas turbine engine combustion chamber includes an annular combustion chamber casing arranged around the combustion chamber. Circumferentially spaced fuel injectors supply fuel into the combustion chamber and a fuel manifold supplies fuel to each of the fuel injectors.
Rolls-royce Plc
01/15/15
20150019104

Gas turbine engine controller with event trigger


A feedback control system is provided and includes a controller to control an operation of a motive element in accordance with current and previous measured states. The controller includes a servo, a processor and an event trigger controller.
General Electric Company
01/15/15
20150017324

Method of applying a nanocrystalline coating to a gas turbine engine component


A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, p, b, tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade.
Pratt & Whitney Canada Corp.
01/15/15
20150017003

Gas turbine engine shrouded blade


A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud.
Rolls-royce Corporation
01/15/15
20150017002

Composite gas turbine engine blade having multiple airfoils


An apparatus includes a composite gas turbine engine multi-airfoil blade that includes first and second circumferentially spaced adjacent composite airfoils coupled together via a common composite attachment. The common attachment does not employ a fastener.
Rolls-royce Corporation
01/15/15
20150016983

Subsonic shock strut


A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a “subsonic shock.” the discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body.
Rolls-royce Corporation
01/15/15
20150016971

Compartmentalization of cooling air flow in a structure comprising a cmc component


A structure in a gas turbine engine comprises a spar and a cmc component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air..
Rolls-royce North American Technologies, Inc.
01/15/15
20150016964

Gas turbine engine and operations


An improved gas turbine engine is adapted to include an inlet flow control arrangement disposed in an inlet passage at least between a filter member and a row of variable inlet guide vanes (vigv), and adjacent the filter member, to enable pressure loss in the inlet passage and supply reduced amount of inlet air to a compressor to enable the reduction of power output of the gas turbine engine at a low load condition.. .
Alstom Technology Ltd
01/15/15
20150016956

Compliant intermediate component of a gas turbine engine


One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component.
Rolls-royce Corporation
01/15/15
20150016949

Tip clearance control method


A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run.
Rolls-royce Plc
01/15/15
20150016946

Blade clearance control for gas turbine engine


An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis.
Rolls-royce North American Technologies, Inc.
01/15/15
20150016945

Liner for gas turbine engine


An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component.
Rolls-royce Corporation
01/15/15
20150016944

Cooled gas turbine engine component


A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole.
Rolls-royce North American Technologies, Inc.


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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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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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