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Gas Turbine patents



      
           
This page is updated frequently with new Gas Turbine-related patent applications. Subscribe to the Gas Turbine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine RSS RSS


Gas turbine engine tip clearance control

Gas turbine engine tip clearance control

Gas turbine engine tip clearance control

Gas turbine engine tip clearance control

Gas turbine engine tip clearance control

Eccentric diaphragm adjusting pins for a gas turbine engine

Date/App# patent app List of recent Gas Turbine-related patents
10/23/14
20140315136
 Methods of operating a gas turbine to inhibit vanadium corrosion patent thumbnailMethods of operating a gas turbine to inhibit vanadium corrosion
A method of inhibiting vanadic corrosion of a hot part of a gas turbine system is provided. The method includes introducing, in the combustor, a first oxide comprising magnesium oxide (mgo) and at least one second oxide from among al2o3, fe2o3, tio2 and sio2.
10/23/14
20140314568
 Gas turbine engine tip clearance control patent thumbnailGas turbine engine tip clearance control
A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor.
10/23/14
20140314567
 Gas turbine engine tip clearance control patent thumbnailGas turbine engine tip clearance control
A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor.
10/23/14
20140314550
 Eccentric diaphragm adjusting pins for a gas turbine engine patent thumbnailEccentric diaphragm adjusting pins for a gas turbine engine
The present invention relates to a stator stage (100) for a gas turbine and a method of adjusting a relative position between a vane segment (110) and a centre section (101) of the stator stage. A groove (102) is formed between a first rim (103) and a second rim (104) of a radially outer edge of the centre section, wherein the groove, the first rim and the second rim run along a circumferential direction (131).
10/23/14
20140314548
 Turbine engine and vane system patent thumbnailTurbine engine and vane system
One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine.
10/23/14
20140314542
 Gas turbine engine exhaust diffuser with movable struts patent thumbnailGas turbine engine exhaust diffuser with movable struts
An exhaust diffuser for a gas turbine engine gas turbine engine includes a multiple of circumferentially spaced struts that extend between an inner gaspath wall and an outer gaspath wall, at least one of the multiple of circumferentially spaced struts movable about a strut axis.. .
10/23/14
20140314540
 Gas turbine engine synchronization ring patent thumbnailGas turbine engine synchronization ring
A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine..
10/23/14
20140312611
 Locking fluid fittings patent thumbnailLocking fluid fittings
A fluid conduit for a gas turbine engine includes a first fluid conduit attachable to a second fluid conduit and securable together with a lockable connector. The connector includes a first portion including external threads and a second portion receiving the first portion and including internal threads mating to the external threads of the first portion.
10/23/14
20140311260
 Gas turbine rotor positioning device patent thumbnailGas turbine rotor positioning device
The invention refers to a device for positioning the rotor of a gas turbine linearly actuating a piston rod that actuates on its end a ratched wheel that moves the rotor of the gas turbine. The device includes an eccentric wheel and a synchronous motor, such that the piston rod is moved through the eccentric wheel, connected to the synchronous motor.
10/23/14
20140311164
 Gas turbine engine and turbine blade patent thumbnailGas turbine engine and turbine blade
One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine.
10/23/14
20140311163
Method of manufacturing a turbomachine component, an airfoil and a gas turbine engine
One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil.
10/23/14
20140311162
Connection structure of exhaust chamber, support structure of turbine, and gas turbine
In a gas turbine, an exhaust casing and an exhaust chamber are connected by an exhaust chamber support that can absorb thermal expansion, and the exhaust chamber and an exhaust duct are connected by an exhaust duct support that can absorb thermal expansion. An insulator is mounted on an outer peripheral surface of the exhaust chamber, and the exhaust chamber support and the exhaust duct support are disposed outside the insulator in the form of a plurality of strips.
10/23/14
20140311157
Vane carrier temperature control system in a gas turbine engine
A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine.
10/23/14
20140311155
Flow splitter for a fluid system of a gas turbine engine
A gas turbine engine is disclosed having a working fluid system capable of moving a working fluid. The working fluid system includes a flow splitter capable of splitting the working fluid into different streams.
10/23/14
20140311154
Flow merging device for a fluid system of a gas turbine engine
A gas turbine engine is disclosed having a working fluid system capable of moving a working fluid. The working fluid system includes a flow union member capable of combining different streams of working fluid.
10/23/14
20140311153
Combustor assembly for a gas turbine engine
A combustor assembly for a gas turbine engine includes a hanger and a combustor liner fixed to the hanger such as, for example, by an annular weld joint. The combustor liner has an inner surface extending along an axis and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber.
10/23/14
20140311152
Reverse flow ceramic matrix composite combustor
A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion.
10/23/14
20140311151
Gas turbine combustor
Provided is a gas turbine combustor having improved maintainability obtained by facilitating the mounting and removal of a base plate for supporting main burners and a pilot burner. A gas turbine combustor is provided with: a pilot burner disposed at the center of a combustor inner tube; main burners provided on the outside of the pilot burner in the radial direction so as to be arranged in the circumferential direction of the inner peripheral surface of the combustor inner tube; a circular disc-shaped base plate disposed within the combustor inner tube and supporting both the pilot burner and the main burners; and an engagement section protruding from the inner peripheral surface toward the inside thereof in the radial direction and engaging with the base plate.
10/23/14
20140311150
Fuel nozzle for a pre-mix combustor of a gas turbine engine
A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage.
10/23/14
20140311149
Gas turbine engine fan blade airfoil profile
A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of cartesian coordinates set forth in table 1.
10/16/14
20140309786
Method for automatic positioning of a gas turbine rotor
A method for positioning a rotor of a gas turbine automatically is provided that includes gathering data with a control unit, and processing this data to bring the rotor to a desired position which is set according a human machine interface (hmi). The indication of the lay of the rotor to the control unit is done by a key phasor, which includes a sensor which gets a digital pulse for each revolution of a phasor cam wheel.
10/16/14
20140308175
Catalytic combustor in gas turbine engine
A catalytic combustor (2) in a gas turbine engine (gt) includes a casing (54) for accommodating a catalyst carrier (10) therein, a catalyst retaining body (62) interposed between the casing (54) and the catalyst carrier (10) for retaining an outer peripheral surface of the catalyst carrier (10) to an inner peripheral surface of the casing (54) and also for preventing a gas (g2) from leaking in a downstream direction through an outer periphery of the catalyst carrier (10), a support material (64) disposed on a downstream side of the direction of flow of the gas to be treated in the catalyst carrier (10) for holding the catalyst carrier (10), and a downstream side regulating member (72) disposed on the downstream side of the catalyst retaining body (62) for avoiding a movement of the catalyst retaining body (62) in a direction of flow of the gas (g2).. .
10/16/14
20140308174
Catalytic combustor in gas turbine engine
A catalytic combustor (2) for use in a gas turbine engine (gt) includes catalyst units (u1, u2, u3) in a multistage. The catalyst unit (u1, u2, u3) in each stage includes a support material (64) for supporting the respective catalyst unit (u1, u2, u3) against the pressure of a gas.
10/16/14
20140308116
Gas turbine thermal shroud with improved durability
Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions located in the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.. .
10/16/14
20140308113
Structure and method for providing compliance and sealing between ceramic and metallic structures
A structure providing compliance and sealing between ceramic or ceramic composite (cmc) part and a metallic part has an interface component for centering the cmc part in the metallic part, thus reducing thermal stress motion of the cmc component. In gas turbine engine applications, the structure comprises a cmc blade track inserted in a clip placed within a metallic hanger.
10/16/14
20140306460
High speed direct drive generator for a gas turbine engine
A motor/generator apparatus for direct coupling to a high rpm, high power shaft is disclosed for one or more of starting and/or extracting power from a gas turbine engine, controlling engine responsiveness, providing a temporary power boost, providing some engine braking and modulating compressor and turbine transient performance as engine power is changed. For example, an axial flux motor/generator configuration is disclosed in which a centrifugal gas compressor rotor is also the rotor of an axial electrical flux motor/generator.
10/16/14
20140305512
Pulsed water flush of liquid fuel valves and combustion nozzles
A method of flushing liquid fuel from valves and nozzles in a gas turbine is conducted via a mixing valve including flow passages for fuel and water. In the method, water is flowed through the flow passages, and the flow is interrupted for a period of no flow.
10/16/14
20140305136
Mounting arrangement
A gas turbine engine is provided that has a rigid dressing raft mounted to a rigid part of the gas turbine engine. The rigid dressing raft includes at least a part of a component or system of the gas turbine engine.
10/16/14
20140305134
Rigid raft for a gas turbine engine
A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft.
10/16/14
20140305132
Method for starting up a gas and steam turbine system
A method for starting a gas and steam turbine system which includes a gas turbine system which includes at least one gas turbine, in addition to at least one steam turbine system which includes at least one steam turbine and at least one steam system is provided. Heat produced by the working fluid and which is released in the gas turbine is guided to the steam system in order to produce steam which drives the steam turbine.
10/16/14
20140305131
Method and device for feeding back exhaust gas from a gas turbine with a downstream waste heat boiler
A method for feeding back exhaust gas from a gas turbine with a downstream waste heat boiler, wherein this exhaust gas is metered into the air inflow stream of a gas turbine, with the result that the temperature and the composition of the exhaust gas can be controlled, and in this way highly concentrated carbon dioxide (co2) is obtained which can be injected into a storage facility, so that the balance of the carbon dioxide for the entire process can be kept low or is negligible. The temperature in the gas turbine can be lowered and the proportion of carbon dioxide in the exhaust gas can be considerably increased.
10/16/14
20140305130
Aircraft environmental control system inlet flow control
A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (egt) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed egt and on the sensed conditioned air temperature..
10/16/14
20140305129
Gas turbine engine support strut assembly
Support strut assembly for supporting a casing of a functional unit of gas turbine is provided having a strut body for supporting the casing to ground, a ball pivot element mounted to the strut body and a rocker lever mounted to the ball pivot element. The rocker lever inserts into a bearing bore of a support body as part of the casing or ground, the rocker lever inserts into the bearing bore via clearance fit so a pivotal point is generated at a first contact area between the rocker lever and an inner surface of the bearing bore, the rocker lever pivots within the bearing bore around the pivotal point.
10/16/14
20140305127
System and method for augmenting gas turbine power output
A system for augmenting gas turbine power output includes a compressed air supply, and a compressed air storage plenum in fluid communication with the compressed air supply. The compressed air storage plenum is configured to store a compressed air from the compressed air supply for later use.
10/16/14
20140305095
Gas turbine combustor
Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame..
10/16/14
20140305094
Gas turbine combustor
Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame..
10/16/14
20140304989
Rotor blade assembly tool for gas turbine engine
A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure.
10/09/14
20140301861
Airfoil having an erosion-resistant coating thereon
A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose.
10/09/14
20140301858
Rotor device, turbine rotor device, and gas turbine and turbine engine having same
Disclosed is a turbine rotor device for a gas turbine, the turbine rotor device comprising a turbine rotor body, and a pre-stressed fiber-wound layer, wherein the pre-stressed fiber-wound layer is wound on the periphery of the turbine rotor body to exert a predetermined pre-loading force on the turbine rotor body. Additionally, a rotor, and a gas turbine and a turbine engine having the turbine rotor device are also provided..
10/09/14
20140301849
Turbine split ring retention and anti-rotation method
A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate.
10/09/14
20140301840
Guide vane arrangement
A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward.
10/09/14
20140301838
Repair of a gas turbine component
A gas turbine component is provided having a repaired vane platform and rail region in which a portion of the vane rail having been damaged during operation is removed. A bar insert is rough machined and is secured within a groove in the rail.
10/09/14
20140301834
Turbine cylinder cavity heated recirculation system
A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system.
10/09/14
20140301820
Turbine engine shutdown temperature control system with nozzle injection for a gas turbine engine
A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine.


Popular terms: [SEARCH]

Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

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This listing is a sample listing of patent applications related to Gas Turbine 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 with additional patents listed. Browse our RSS directory or Search for other possible listings.
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