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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


Edge seal for gas turbine engine ceramic matrix composite component

Gas turbine engine variable geometry flow component

Gas turbine engine system and supersonic exhaust nozzle

Date/App# patent app List of recent Gas Turbine Engine-related patents
08/28/14
20140244132
 System and method for 0n-wing engine trim verification patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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.. .
08/28/14
20140241899
 Blade leading edge tip rib patent thumbnailnew patent Blade leading edge tip rib
A rotor blade for a gas turbine engine includes a leading edge tip rib projecting outwardly from an airfoil of the blade at a tip region thereof. The tip rib continuously surrounds a leading edge of the airfoil and extends rearwardly from the leading edge along respective pressure and suction side surfaces to thereby alter the blade tip leakage vortex structure and strength, resulting in a stage efficiency benefit..
08/28/14
20140241890
 Gas turbine engine blade and disk patent thumbnailnew patent Gas turbine engine blade and disk
In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.. .
08/28/14
20140241883
 Gas turbine engine component patent thumbnailnew patent Gas turbine engine component
Embodiments are disclosed of a turbomachinery component having an outer part that is captured between a cap and a base of the component. In one form, the outer part is placed in compression between the cap and the base.
08/28/14
20140241863
 Exhaust section for bypass gas turbine engines patent thumbnailnew patent Exhaust section for bypass gas turbine engines
A turbine exhaust section comprises a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer projecting axially rearwardly from the turbine exhaust case for mixing the hot exhaust gases with a cooler bypass duct flow. The upstream end of the exhaust mixer surrounds a downstream end of the outer duct and defines therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer.
08/28/14
20140241857
 Flow diverter to redirect secondary flow patent thumbnailnew patent Flow diverter to redirect secondary flow
An assembly for a gas turbine engine includes a seal and a flow diverter. The flow diverter is disposed adjacent the seal to direct a secondary gas flow that passes across the seal away from a rotor cavity such that the secondary gas flow travels back toward a main gas flow path of the gas turbine engine..
08/28/14
20140241856
 Gas turbine engine systems involving tip fans patent thumbnailnew patent Gas turbine engine systems involving tip fans
Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades..
08/28/14
20140241854
new patent Active turbine or compressor tip clearance control
A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted..
08/28/14
20140241852
new patent Methods and apparatus for measuring axial shaft displacement within gas turbine engines
In some embodiments, an apparatus includes a target member, a sensor and a mounting assembly. The target member is coupled to a shaft that is disposed within an engine housing and that rotates about an axis.
08/28/14
20140241851
new patent Axial oil scoop for a gas turbine engine
An axial oil scoop for a gas turbine engine includes an outer surface with a concave profile, the outer surface includes a multiple of radial holes.. .
08/28/14
20140241850
new patent Air particle separator
A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator.
08/28/14
20140239638
new patent Method for providing a frequency response for a combined cycle power plant
The disclosure refers to a method for providing a frequency response for a combined cycle power plant connected to an electric grid. The combined cycle power plant includes a gas turbine engine and a steam turbine engine.
08/28/14
20140238043
new patent Gas turbine engine system and supersonic exhaust nozzle
One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine.
08/28/14
20140238042
new patent Gas turbine engine buffer system
A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine.
08/28/14
20140238040
new patent Combined cycle power plant
A combined cycle engine is used to provide power to a vehicle. In one form the combined cycle engine includes two engines coupled through a gearbox.
08/28/14
20140238038
new patent Gas turbine variable focus laser ignition
A laser ignition system for a gas turbine engine includes a combustion chamber. The system comprises a laser source for generating a continuous laser beam during an ignition process of the combustion chamber; and a dynamic laser focus apparatus positioned outside of the combustion chamber and focusing the laser beam into a continuously varying focal point to generate a laser kernel moving within a spray of air/fuel mixture injected into the combustion chamber..
08/28/14
20140238037
new patent Gas turbine engine and method for operating a gas turbine engine
One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine.
08/28/14
20140238035
new patent Method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine
The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (ch4), ethane (c2h6), propane (c3h8), butane (c4h10), carbon dioxide (co2), calculating the nitrogen (n2) percentage content as the complement to 100 of the measured percentage content of methane (ch4), ethane (c2h6), propane (c3h8), butane (c4h10), carbon dioxide (co2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.. .
08/28/14
20140238033
new patent Systems and methods to control combustion dynamic frequencies
Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency..
08/28/14
20140238029
new patent Flow conditioner in a combustor of a gas turbine engine
A combustor in a gas turbine includes a liner having an interior volume defining a main combustion zone, a fuel injection system for delivering fuel into the main combustion zone, and a flow sleeve that defines, with the liner, a passageway for air to flow on its way to be mixed with fuel from the fuel injection system, wherein the mixture is burned in the main combustion zone to create hot combustion gases. The combustor further includes a flow conditioner including at least one panel having a configuration such that air is able to pass through the panel(s) on its way to the passageway, wherein at least a substantial portion of the air that enters the passageway for being burned in the main combustion zone passes through the panel(s)..
08/28/14
20140238027
new patent Thermally compliant dual wall liner for a gas turbine engine
A stiffener for a liner assembly of a gas turbine engine includes a second resilient member arranged on a first resilient member at substantially ninety (90) degree orientation.. .
08/28/14
20140237990
new patent Variable area fan nozzle with wall thickness distribution
A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section.
08/28/14
20140237989
new patent Laser-ignition combustor for gas turbine engine
The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner..
08/28/14
20140237987
new patent Gas turbine engine variable geometry flow component
A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine.
08/21/14
20140236450
Determining the deterioration of a gas turbine engine in use
This invention provides a method and apparatus to identify fod or bird impact to gas turbine fan blades, assessing the damage that may have occurred whist still in flight and determining post impact actions, including replacement parts.. .
08/21/14
20140235426
Ceramic powders and methods therefor
A ceramic powder and method of forming the ceramic powder capable of being used in coatings to allow components to survive in high temperatures environments, such as the hostile thermal environment of a gas turbine engine. The ceramic powder includes powder particles each having an inner core formed of a first material and an outer region formed of a second material.
08/21/14
20140234118
Turbine engine comprising a metal protection for a composite part
A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.. .
08/21/14
20140234112
Rotor blade
A blade at least part of which is arranged in use to rotate outside of a casing of a gas turbine engine. The blade has a main body, a tip fence and a blend region defining a curve between the main body and the fence.
08/21/14
20140234082
Bumper for synchronizing ring of gas turbine engine
A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle.
08/21/14
20140234079
Geared architecture for high speed and small volume fan drive turbine
A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system..
08/21/14
20140234078
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan.
08/21/14
20140230943
Support system bumper for exhaust duct liner hanger
A hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a pin and a bumper. The first bracket is for connecting to an exhaust duct or liner of the gas turbine exhaust system.
08/21/14
20140230452
Planetary gear system arrangement with auxiliary oil system
In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input.
08/21/14
20140230441
Heat shield manifold system for a midframe case of a gas turbine engine
A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required.
08/21/14
20140230404
Gas turbine engine exhaust mixer
An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring.
08/21/14
20140230403
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 flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path.
08/21/14
20140230400
Heat retention and distribution system for gas turbine engines
A gas turbine engine including a compressor section, a combustor section, and a turbine section operating to produce a power output during a first mode of operation. A heat retention and distribution system is provided to the engine wherein the heat retention system operates in a second mode of operation, following a shutdown of the engine, to maintain an elevated temperature in components of each of the compressor section, the combustor section and the turbine section in order to effect (1) a reduction in an effective cyclic life consumption of the components and extend a maintenance interval associated with the effective cyclic life consumption, and (2) clearances by maintaining a higher vane carrier temperature with time during a non-power producing mode and more uniform temperature of most stationary components in the circumferential orientation..
08/21/14
20140230246
Thermally free hanger with length adjustment feature
A system for connecting spaced components of a gas turbine engine includes connecting one end of a t-bar to each of the spaced components. One component is attached to the crossbar portion of the t-bar by trapping the crossbar between the component and a bracket.
08/14/14
20140227093
Low 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
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
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
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
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
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
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
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
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
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.


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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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