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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


Blade outer air seal surface

Mid-turbine frame vane assembly support with retention unit

Fan containment system

Date/App# patent app List of recent Gas Turbine Engine-related patents
08/14/14
20140227093
 Low profile thermally free blind liner hanger attachment for complex shapes patent thumbnailLow profile thermally free blind liner hanger attachment for complex shapes
A hanger system for connecting components in a gas turbine engine has a first spaced component, a second spaced component arranged a desired distance from the first spaced component, and a plurality of spacers arranged between the first spaced component and the second spaced component. A t-bar having a shaft portion and a crossbar is arranged between the components.
08/14/14
20140227087
 Blade outer air seal surface patent thumbnailBlade outer air seal surface
A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile..
08/14/14
20140227078
 Mid-turbine frame vane assembly support with retention unit patent thumbnailMid-turbine frame vane assembly support with retention unit
A mid-turbine frame for a gas turbine engine includes a vane assembly supported within a case. The vane assembly directs airflow between a first turbine and a second turbine.
08/14/14
20140227076
 Fan containment system patent thumbnailFan containment system
A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub..
08/14/14
20140223920
 Consumable assembly mistake proofing tool for a gas turbine engine patent thumbnailConsumable assembly mistake proofing tool for a gas turbine engine
A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine. .
08/14/14
20140223919
 Flexible liner hanger patent thumbnailFlexible liner hanger
A gas turbine engine exhaust system includes a liner extending along an axial direction and a radial direction and circumscribing a combustion plenum, a high pressure plenum circumscribing the liner along the radial direction, a structural component circumscribing the high pressure plenum along the radial direction, and a leaf spring fastener arranged within the high pressure plenum. The leaf spring fastener is arranged between the liner and the structural component..
08/14/14
20140223916
 Gas turbine engine with compressor inlet guide vane positioned for starting patent thumbnailGas turbine engine with compressor inlet guide vane positioned for starting
A gas turbine engine includes a compressor section, the compressor section including a variable inlet guide vane which is movable between distinct angles to control the airflow approaching the compressor section. A control is programmed to position the vane at startup of the engine to direct airflow across the compressor section.
08/14/14
20140223914
 Flow sleeve inlet assembly in a gas turbine engine patent thumbnailFlow sleeve inlet assembly in a gas turbine engine
A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway.
08/14/14
20140223913
 Forged fuel injector stem patent thumbnailForged fuel injector stem
A gas turbine engine fuel injector stem includes a single piece of material with a flange, a center body, a gas gallery, and a fluid passage. The flange includes a cylindrical shape, a plurality of mounting holes and a handle hole.
08/14/14
20140223737
 Material removal method patent thumbnailMaterial removal method
A repair method for repairing a component (6a) of a gas turbine engine (10). The method comprises first and second steps.
08/07/14
20140219817
High pressure turbine blade cooling hole distribution
A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered pa-1 to pa-10, pb-1 to pb-3, ha-1 to ha-9, and sa-1 to sa-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the x, y, z cartesian coordinate values set forth in table 3..
08/07/14
20140219816
High pressure turbine blade cooling hole distribution
A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered pa-1 to pa-10, pb-1 to pb-3, ha-1 to ha-9, and sa-1 to sa-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the x, y, z cartesian coordinate values set forth in table 3..
08/07/14
20140219815
Multi-lobed cooling hole
A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet.
08/07/14
20140219813
Gas turbine engine serpentine cooling passage
A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls.
08/07/14
20140219811
Twisted gas turbine engine airfoil having a twisted rib
A gas turbine engine blade (20), including: an airfoil (24) including a pressure side exterior surface (34), a suction side exterior surface (36), and a first rib (130) spanning between the pressure side exterior surface and the suction side exterior surface. The airfoil (24) is twisted from a base end (30) of the airfoil to a tip end (32) of the airfoil.
08/07/14
20140219809
Casting core for twisted gas turbine engine airfoil having a twisted rib
A casting core (200) for a twisted gas turbine engine blade, including: an airfoil portion (202) having: an airfoil base end (208), an airfoil tip end (210), a concave side exterior surface (212), a convex side exterior surface (214), a leading edge (204), and a trailing edge (206). The airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end.
08/07/14
20140219807
Under-root spacer for gas turbine engine fan blade
A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot.
08/07/14
20140219805
Low radius ratio fan for a gas turbine engine
A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.. .
08/07/14
20140219794
Bore cavity thermal conditioning system
A gas turbine engine includes a rotor having at least one rotor bore cavity and a heat exchanger. The heat exchanger is fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the conditioning air source to the rotor bore cavity.
08/07/14
20140219792
Pylon matched fan exit guide vane for noise reduction in a geared turbofan engine
A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades.
08/07/14
20140219785
Vane arm having a claw
An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem..
08/07/14
20140219783
Gas turbine engine fan drive gear system damper
A gas turbine engine includes a fan section, a turbine section coupled to the fan section through a geared architecture, a first member supporting the geared architecture, and a second member supporting the first member relative to an engine static structure. The first member and the second members are spaced apart from one another at a location.
08/07/14
20140219778
Gas turbine engine airfoil with vane platform cooling passage
A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform.
08/07/14
20140216054
Variable volume combustor with aerodynamic support struts
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles.
08/07/14
20140216053
Geared turbofan gas turbine engine with reliability check on gear connection
A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor.
08/07/14
20140216051
Variable volume combustor with an air bypass system
The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner.
08/07/14
20140216050
Variable volume combustor with nested fuel manifold system
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system..
08/07/14
20140216049
Variable volume combustor with pre-nozzle fuel injection system
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system..
08/07/14
20140216048
Variable volume combustor
The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner..
08/07/14
20140216044
Gas turbine engine combustor heat shield with increased film cooling effectiveness
A heat shield for a gas turbine engine includes a hot side with one or more raised features that extend therefrom.. .
08/07/14
20140216043
Combustor liner for a can-annular gas turbine engine and a method for constructing such a liner
A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32) a cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner a property of the cooling channel may be varied along a length of the cooling channel.
08/07/14
20140216041
Variable volume combustor with center hub fuel staging
The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles.
08/07/14
20140216040
Variable volume combustor with a conical liner support
The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner..
08/07/14
20140216039
Variable volume combustor with aerodynamic fuel flanges for nozzle mounting
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles.
08/07/14
20140216038
Variable volume combustor with cantilevered support structure
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within an end cover, a common fuel tube extending through the end cover and in communication with the micro-mixer fuel nozzles, a linear actuator to maneuver the common fuel tube and the micro-mixer fuel nozzles, and a sealing support structure positioned between the end cover and the common fuel tube..
08/07/14
20140216036
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).
08/07/14
20140216005
Gas turbine engine assembly including a thrust reverser
An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position..
08/07/14
20140216004
Compressed air bleed supply for buffer system
A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet.
08/07/14
20140216003
Gas turbine engine with geared turbofan and oil thermal management system
A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section.
08/07/14
20140216002
Gas turbine engine having slim-line nacelle
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area.
08/07/14
20140215998
Gas turbine engines with improved compressor blades
A rotor blade for a compressor includes a pressure sidewall; a suction sidewall coupled to the pressure sidewall at a leading edge and a trailing edge; and a through hole extending between the pressure sidewall and the suction sidewall.. .
08/07/14
20140215997
Flexible shield for fluid connectors
A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector.
07/31/14
20140212298
Gas turbine engine turbine blade tip cooling
An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge.
07/31/14
20140212297
Gas turbine engine serpentine cooling passage with chevrons
A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions.
07/31/14
20140212295
Spinner assembly with removable fan blade leading edge fairings
A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings.
07/31/14
20140212292
Airfoil member and composite platform having contoured endwall
An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics.
07/31/14
20140212284
Hybrid turbine nozzle
A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands.. .
07/31/14
20140212270
Gas turbine engine component having suction side cutback opening
An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the pressure side wall and each extending between a leading edge portion and a trailing edge portion. A plurality of cutback openings are spaced along a radial axis of the suction side wall..
07/31/14
20140212261
Lightweight shrouded fan
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.. .
07/31/14
20140209408
Exhaust cone
A gas turbine engine exhaust cone (40) comprising one or more acoustic absorption chambers (48), each chamber (48) comprising two side walls (50) and an acoustic attenuation wall (62). The side walls (50) define the circumferential extent of the chamber (48).
07/31/14
20140209286
Gas turbine engine integrated heat exchanger
A heat exchanger apparatus including at least one cooling channel formed within and about an engine booster lip or an engine nacelle and configured to receive a flow of a circulating working fluid; and at least one fluid port communicating with the at least one cooling channel and an exterior of the engine booster lip or the engine nacelle.. .
07/31/14
20140209124
Gas turbine offline compressor wash with buffer air from combustor
A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor..
07/31/14
20140209123
Compressor wash with air to turbine cooling passages
A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor..
07/31/14
20140208837
Gas turbine engine vane embedded beam interrupt optical tip-timing probe system
A method of observing an airflow passage within a gas turbine engine includes locating a support in view of an airflow passage and housing an optical fiber within the support.. .
07/31/14
20140208771
Gas turbine engine component cooling arrangement
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion having an exterior surface and an internal surface. A cavity is disposed inside of the body portion.
07/31/14
20140208768
Coolant supply system
A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section.
07/31/14
20140208762
Compressor wash with air to bearing buffering system
A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor..
07/31/14
20140208760
Gas turbine engine with transmission
A gas turbine engine with a transmission having a first rotatable member coupled to an engine spool, a second rotatable member coupled to a compressor rotor, and coupled rotatable members defining at least first and second alternate transmission paths between the first and second members. Each transmission path defines a different fixed transmission ratio of a rotational speed of the second member on a rotational speed of the first member..
07/31/14
20140208759
Apparatus and method for reducing oil mist ingestion in a heavy duty gas turbine engine
A lubrication system for a heavy duty gas turbine includes a bearing lubrication assembly coupled to the bearing and an oil and vapor extraction assembly disposed in a cavity defined by a bell mouth hood in an air inlet duct. A high volume vacuum blower is coupled to the oil and vapor extraction assembly to provide a relative negative pressure.
07/31/14
20140208757
Air/fuel supply system for use in a gas turbine engine
A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure.
07/31/14
20140208755
Gas turbine air mass flow measuring system and methods for measuring air mass flow in a gas turbine inlet duct
A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct.
07/31/14
20140208714
Thermal management for gas turbine engine
A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine..
07/24/14
20140205449
Superalloys and components formed thereof
A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine.
07/24/14
20140205443
Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane the grooves are arranged such that a circumferential space is defined between adjacent grooves during operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path..
07/24/14
20140205441
Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface.
07/24/14
20140205439
Gas turbine engine shaft bearing configuration
A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case.
07/24/14
20140205438
Relationship between fan and primary exhaust stream velocities in a geared gas turbine engine
An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an exhaust velocity ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90..
07/24/14
20140205424
Systems and methods to control variable stator vanes in gas turbine engines
Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring.
07/24/14
20140202166
Method of operating a gas turbine for reduced ammonia slip
Described herein are methods of operating a gas turbine engine (12) for reduced ammonia slip. An exemplary method (100) includes operating (102) the engine over a range of power output levels; controlling (104) a mass flow of nox produced in exhaust (19) of the engine to be within 10% over the range of power output levels; and treating (106) the exhaust of the engine in a selective catalytic reduction process (22).
07/24/14
20140202164
Gas turbine engine nozzle including housing having scalloped root regions
A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons.
07/24/14
20140202160
Gas turbine system with manifold
A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.. .
07/24/14
20140202158
Gas turbine engine heat exchangers and methods of assembling the same
A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel.
07/24/14
20140202133
Gas turbine engine mid turbine frame with flow turning features
A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage.


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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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