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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


Mounting system for a planatary gear train in a gas turbine engine

Lubrication oil system for a reduction gearbox

Aerodynamic fairings secondarily attached to nosecone

Date/App# patent app List of recent Gas Turbine Engine-related patents
09/11/14
20140257542
 System and method for positioning error compensation during manufacturing of complex-shaped gas turbine engine parts patent thumbnailSystem and method for positioning error compensation during manufacturing of complex-shaped gas turbine engine parts
A system and method for error compensation in positioning a complex-shaped gas turbine engine part during manufacturing thereof with a machine. Theoretical measurements for a plurality of control points on the part are first retrieved.
09/11/14
20140256504
 Mounting system for a planatary gear train in a gas turbine engine patent thumbnailMounting system for a planatary gear train in a gas turbine engine
A mounting system for a planetary gear train in a gas turbine engine comprises a support strut, a deflection flange and a deflection limiter. The support strut extends between a stationary engine case and a rotating engine shaft that provides input to the planetary gear train in the gas turbine engine.
09/11/14
20140256494
 Lubrication oil system for a reduction gearbox patent thumbnailLubrication oil system for a reduction gearbox
A reduction gear box is part of a gas turbine engine and includes a casing and reduction epicyclic gear stages within the casing. The reduction gear stages comprising at least an epicyclic array of gears meshing together with at least one planetary gear mounted for rotation on a gear carrier and a bearing associated therewith.
09/11/14
20140255204
 Aerodynamic fairings secondarily attached to nosecone patent thumbnailAerodynamic fairings secondarily attached to nosecone
An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy.
09/11/14
20140255197
 Rotor blades for gas turbine engines patent thumbnailRotor blades for gas turbine engines
A rotor dual-blade for a gas turbine engine that has a first blade component extending radially between a root and a tip and a second blade component, separate from the first component, extending radially between a root and a tip, wherein the second blade component is downstream, in series, of the first blade component and at least the first blade component is made of metal while the second blade component is a light weight composite material.. .
09/11/14
20140255196
 Double split blade lock ring patent thumbnailDouble split blade lock ring
A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade.
09/11/14
20140255188
 Gas turbine engine airflow member having spherical end patent thumbnailGas turbine engine airflow member having spherical end
A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade.
09/11/14
20140255187
 Attachment feature of a gas turbine engine blade having a curved profile patent thumbnailAttachment feature of a gas turbine engine blade having a curved profile
An airfoil member is disclosed having an attachment feature such as a fir tree or dovetail design that includes a curved profile formed from a combination of curves. In one embodiment, the curved profile can be a compound curve formed by a forward curve and a rearward curve that are joined at a point of common tangency.
09/11/14
20140255182
 Push-lock pin connector patent thumbnailPush-lock pin connector
A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.. .
09/11/14
20140255181
 Gas turbine engine diffuser system for a high pressure (hp) compressor patent thumbnailGas turbine engine diffuser system for a high pressure (hp) compressor
A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller.
09/11/14
20140255177
Outboard insertion system of variable guide vanes or stationary vanes
A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture.
09/11/14
20140255174
Manufacture of full ring strut vane pack
A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform.
09/11/14
20140255172
Low profile push-lock device
A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism.. .
09/11/14
20140255170
Cmc turbine engine component
A component of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (cmc). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine.
09/11/14
20140255168
Inter-module flow discourager
An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint.
09/11/14
20140255167
Consumable assembly tool for a gas turbine engine
A method of assembling a gas turbine engine includes locating a consumable assembly tool within the engine. .
09/11/14
20140255162
Adjustable floating oil channel for gas turbine engine gear drive
A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan.
09/11/14
20140255158
Coating process for gas turbine engine component with cooling holes
A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the. .
09/11/14
20140255156
Non-contacting seals for geared gas turbine engine bearing compartments
A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment.
09/11/14
20140255152
Fan track liner designed to yield next to fan case hook
A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure.
09/11/14
20140255148
Gas turbine engine clearance control
One embodiment of the present disclosure is a unique gas turbine engine having a bearing system and method of operating the engine. Another embodiment is a unique rotor machine.
09/11/14
20140254631
Actively cooled gas turbine sensor probe housing
An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path.
09/11/14
20140252769
Gas turbine engine with internal electromechanical device
A gas turbine engine including high and low pressure shafts, an electromechanical device having a rotor and a stator coupled such that the rotor is rotatable with respect to the stator, the rotor having a device gear secured thereto, the device being secured to a support structure in a bearing housing forming part of a bearing assembly supporting a portion of the low pressure shaft extending in proximity of the high pressure shaft and of the shaft gear, and a coupling idle gear secured for rotation about a stationary gear support mounted in the bearing housing, the idle gear being in toothed engagement with the shaft gear and with the device gear. An electromechanical device assembly for a gas turbine engine and a method of operating an electromechanical device are also provided..
09/11/14
20140252167
Reverse core engine thrust reverser for under wing
A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis.
09/11/14
20140252160
Reverse flow gas turbine engine removable core
An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.. .
09/11/14
20140252159
Engine installation
A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other..
09/11/14
20140250917
Combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly
A gas turbine engine combustion chamber heat shield and seal assembly comprises a heat shield and a seal. The heat shield has an aperture and the seal is located in the aperture in the heat shield.
09/11/14
20140250916
System and method for aligning a gas turbine engine
A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response.
09/11/14
20140250914
Starter motor shared lubrication system
A starter motor has a housing. The housing receives the starter motor and a plurality of locations to receive lubricant.
09/11/14
20140250907
Gas turbine fuel injector with metering cavity
A fuel injector for a gas turbine engine may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery extending circumferentially around the flow path. The fuel gallery may be adapted to inject a liquid fuel into the flow path.
09/11/14
20140250904
Capacity control of turbine by the use of a reheat combustor in multi shaft engine
One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and a second turbine, which is disposed downstream of the reheat combustor.
09/11/14
20140250903
Cogen heat load matching through reheat and capacity match
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of nozzle guide vanes. The reheat combustor is configured to increase a fuel flow so as to increase a temperature of the reheat combustor and match a required exhaust temperature.
09/11/14
20140250902
Compressed air injection system method and apparatus for gas turbine engines
This invention relates to electrical power systems, including generating capacity of a gas turbine, and more specifically to augmentation of power output of gas turbine systems, that is useful for providing additional electrical power during periods of peak electrical power demand.. .
09/11/14
20140250899
Gas turbine engine thermally controlled flow device
An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion.
09/11/14
20140250897
Tip-controlled integrally bladed rotor for gas turbine engine
An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim.
09/11/14
20140250895
Modulated ejector cooling
A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine.
09/11/14
20140250894
Dual-wall impingement, convection, effusion (dice) combustor tile
A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor.
09/11/14
20140250863
Rear mounted reverse core engine thrust reverser
In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis.
09/11/14
20140250862
Reverse flow gas turbine engine airflow bypass
A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.. .
09/11/14
20140250860
Multi-shaft gas turbine engine
A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts.. .
09/11/14
20140250857
Low-concentration methane gas oxidation system using exhaust heat from gas turbine engine
A low-concentration methane gas oxidation system is provided which effectively uses exhaust heat from a gas turbine engine and is able to avoid burnout of a catalyst etc. To enable stable operation even when a methane concentration in a low-concentration methane gas which is a treatment target is rapidly increased.
09/04/14
20140248425
Air cooled gas turbine components and methods of manufacturing and repairing same
A method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area. In a further aspect, a method of repairing a component suitable for use in a gas turbine engine, the method comprising the steps of removing coatings from the component, repairing any defects in the substrate of the component, and applying coatings as described herein..
09/04/14
20140248152
Plate for directing flow and film cooling of components
An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface.
09/04/14
20140248142
Gas turbine engine impeller system for an intermediate pressure (ip) compressor
A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase.
09/04/14
20140248136
Multifunction positioning lock washer
A gas turbine engine section comprises a rotatable shaft, first and second axially adjacent components, a nut, and a multifunction positioning lock washer. The first and second axially adjacent components are located on the rotatable shaft and are separated by an axial separation distance.
09/04/14
20140248133
Active bypass flow control for a seal in a gas turbine engine
An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears in at least one embodiment, the metering device may include an annular ring having at least one metering orifice extending therethrough, whereby alignment of the metering orifice with the outlet may be adjustable to change a cross-sectional area of an opening of aligned portions of the outlet and the metering orifice.
09/04/14
20140248132
Active bypass flow control for a seal in a gas turbine engine cross-reference to related application
An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears.
09/04/14
20140248129
Lpc flowpath shape with gas turbine engine shaft bearing configuration
A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis.
09/04/14
20140248127
Turbine engine component with dual purpose rib
An assembly for a gas turbine engine includes a component, a fairing, and a seal. The fairing is disposed adjacent to the component and defines a primary gas flow path.
09/04/14
20140248126
Inter-module finger seal
An assembly for a gas turbine engine includes a first module, a second module, and a finger seal. The second module is connected to the first module along a joint.
09/04/14
20140248122
High pressure compressor thermal management
A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.. .
09/04/14
20140248121
Aircraft power system
A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere.
09/04/14
20140248120
Bi-metal strip-seal
An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path.
09/04/14
20140248119
Bifurcated inlet scoop for gas turbine engine
A bifurcated inlet scoop frame for a gas turbine engine and method of using such frame for a gas turbine engine are disclosed. The bifurcated inlet scoop frame may include a nose, a first side panel, and a second side panel.
09/04/14
20140246864
Gas turbine engine
One embodiment of the present disclosure is a unique gas turbine engine having an electrical machine for generating electrical power. Other embodiments include other unique gas turbine engines having electrical machines for generating electrical power.
09/04/14
20140246514
Turbomachine thrust reverser
An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine.
09/04/14
20140245753
Gas turbine engine rotor blade
A rotor blade for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil extending in span between a root region and a tip region and a tip portion extending at an angle from the tip region of the airfoil.. .
09/04/14
20140245751
Passages to facilitate a secondary flow between components
An annular mount for a gas turbine engine includes a first flange and a second flange. The first flange has an arcuate shape, and the second flange extends from the first flange.
09/04/14
20140245750
Circumferentially retained fairing
An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount.
09/04/14
20140245749
Nacelle anti-ice valve utilized as compressor stability bleed valve during starting
A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing.
09/04/14
20140245748
Gas turbine engine optimization by electric power transfer
A method of increasing the operational efficiency of an operating gas turbine engine includes supplying mechanical power from a first spool of the operating gas turbine engine to a first electrical machine to thereby generate electrical power using the first electrical machine and supplying mechanical power from a second spool of the operating gas turbine engine to a second electrical machine to thereby generate electrical power using the second electrical machine. The method further includes sensing one or more operational parameters of the operating gas turbine engine and, based on the one or more sensed operational parameters, ceasing to generate electrical power using the second electrical machine, and instead supplying at least a part of the electrical power generated by the first electrical machine to the second electrical machine to operate in motoring mode and to thereby generate and supply mechanical output power to the second spool of the engine..
09/04/14
20140245747
Gas turbine engine two degree of freedom variable bleed valve for ice extraction
A gas turbine engine variable bleed apparatus includes a variable bleed valve door disposed in a bleed inlet in a transition duct, rotatable about two or more separate pivot points, operable to open and close an aft bleed slot extending outwardly from transition duct, and operable to open and close a forward bleed slot extending inwardly into transition duct. Door is operable to transition between a first position with aft bleed slot open and forward bleed slot closed to a second position with aft bleed slot closed and forward bleed slot open without fully closing door.
09/04/14
20140245745
Fuel system of gas turbine engines
A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.. .
09/04/14
20140245744
Control of gas turbine engine
Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters.. .
09/04/14
20140245742
Air swirlers
A swirler, such as for swirling air in a fuel injector of a gas turbine engine, includes a swirler body with opposed inlet and outlet ends with a swirler wall extending therebetween along a longitudinal axis. The inlet end of the swirler body defines an inlet opening.
09/04/14
20140245741
Stator vane row
In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections.
09/04/14
20140245740
Combustor apparatus in a gas turbine engine
A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member.
09/04/14
20140245739
Fuel system of gas turbine engines
A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.. .
08/28/14
20140244132
System and method for 0n-wing engine trim verification
Devices and methods relating to gas turbine engines and engine temperature trim verification are disclosed. An exemplary method comprises acquiring signals representing a plurality of engine parameters measured while the engine is operating and determining a recommended trim thermocouple resistance based at least partly on the measured parameters.
08/28/14
20140242483
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). The solid oxide fuel cell stack (12) comprises a plurality of solid oxide fuel cells (16).
08/28/14
20140242348
Edge seal for gas turbine engine ceramic matrix composite component
A gas turbine engine ceramic matrix composite (cmc) component includes first and second outer layers of plies, and an intermediate layer of plies between the first and second outer layers of plies. The intermediate layer of plies is offset relative to the first and second outer layers of plies.
08/28/14
20140242278
Split coating mask system for gas turbine engine component
A mask assembly for a gas turbine engine component includes a second mask that at least partially overlaps a first mask to fit a platform of a gas turbine engine component.. .


Popular terms: [SEARCH]

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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