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Gas Turbine patents



      
           
This page is updated frequently with new Gas Turbine-related patents. Subscribe to the Gas Turbine RSS feed to automatically get the update: related Gas RSS feeds.

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Date/App# patent app List of recent Gas Turbine-related patents
04/17/14
20140105737
 Gas turbine engine comprising three rotary bodies patent thumbnailnew patent Gas turbine engine comprising three rotary bodies
A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade..
04/17/14
20140105732
 Labyrinth seal for gas turbine engine turbine patent thumbnailnew patent Labyrinth seal for gas turbine engine turbine
A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.. .
04/17/14
20140105731
 Axial seal in a casing structure for a fluid flow machine patent thumbnailnew patent Axial seal in a casing structure for a fluid flow machine
A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls.
04/17/14
20140105725
 Fish mouth seal carrier patent thumbnailnew patent Fish mouth seal carrier
A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile.
04/17/14
20140105723
 Gas turbine diffuser blowing method and corresponding diffuser patent thumbnailnew patent Gas turbine diffuser blowing method and corresponding diffuser
A diffuser of a compressor of centrifugal or mixed type includes two end plates which enclose a plurality of regularly distributed circumferential blades, and at least one transverse upstream passage produced in lower or upper surfaces of the blades. An injection/withdrawal coupling is achieved by a recirculation of a stream in an air passage of the diffuser on the basis of injection of air from at least one point in a leading edge zone of an upstream side of the diffuser.
04/17/14
20140102802
 Center discharge gas turbodrill patent thumbnailnew patent Center discharge gas turbodrill
A compact gas turbine motor and a speed reduction transmission capable of providing the speed and torque required for drilling with center discharge bits. The transmission includes two sun gears of different pitch diameters, keyed to the turbine shaft.
04/17/14
20140102209
 Enhanced static-dynamic pressure transducer suitable for use in gas turbines and other compressor applications patent thumbnailnew patent Enhanced static-dynamic pressure transducer suitable for use in gas turbines and other compressor applications
This disclosure provides example methods, devices and systems associated with filter structures employed with sensors. In one embodiment, a method comprises receiving, at a first filter having a plurality of pores, a pressure, wherein the pressure includes a static pressure component and a dynamic pressure component; filtering, by the first filter, at least a portion of the dynamic pressure component of the pressure; outputting, from the first filter, a filtered pressure; and wherein the filtered pressure is used to determine the dynamic pressure component..
04/17/14
20140102113
 Exhaust heat recovery for a gas turbine system patent thumbnailnew patent Exhaust heat recovery for a gas turbine system
A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into exhaust gases.
04/17/14
20140102111
 Systems and methods for distributing torque contribution patent thumbnailnew patent Systems and methods for distributing torque contribution
Systems and methods for distributing torque contribution are provided. According to one embodiment, a system may include a controller and a processor communicatively coupled to the controller.
04/17/14
20140102110
 Mid-turbine frame with tensioned spokes patent thumbnailnew patent Mid-turbine frame with tensioned spokes
A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a first spoke connecting the outer frame case to the inner frame case. The first spoke is tightened so as to be in tension during substantially all operating conditions of the gas turbine engine..
04/17/14
20140102108
new patent Seal assembly for liners of exhaust nozzle
An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly. .
04/17/14
20140102107
new patent Housing structure with improved seal and cooling
A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall.
04/17/14
20140102071
new patent System and method for heating fuel in a combined cycle gas turbine
A system for heating fuel in a combined cycle gas turbine includes a fuel heat exchanger downstream from a turbine outlet, and the fuel heat exchanger has an exhaust gas inlet, an exhaust gas outlet, a fuel inlet, and a fuel outlet. A first exhaust gas plenum has a first exhaust gas inlet connection between the turbine outlet and a heat exchanger and a first exhaust gas outlet connection upstream from the exhaust gas inlet.
04/17/14
20140101939
new patent Method of fabricating integrally bladed rotor and stator vane assembly
A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced..
04/17/14
20140101938
new patent Method of working a gas turbine engine airfoil
A method of working a gas turbine engine component, for example, a turbine airfoil platform having a heat crack, is disclosed. The presented method may allow turbine airfoils to be repaired, modified, manufactured or otherwise worked and subsequently assembled into a turbine section of a gas turbine engine.
04/10/14
20140100703
Method for the computer-supported generation of a data-driven model of a technical system, in particular of a gas turbine or wind turbine
A method for the computer-supported generation of a data-driven model of a technical system, in particular of a gas turbine or wind turbine, based on training data is disclosed. The data-driven model is preferably learned in regions of training data having a low data density.
04/10/14
20140099210
System for gas turbine rotor and section coupling
A system, including a first turbomachine rotor disk, a first annular protrusion with a first spline coupled to the first turbomachine rotor disk, a second turbomachine rotor disk, and a second annular protrusion with a second spline coupled to the second turbomachine rotor disk, wherein the first and second splines are coupled to one another.. .
04/10/14
20140099209
Gas turbine component, method for its production and casting mold for use of this method
A method is provided for casting a gas turbine component having at least a first section and a second section. As per the method, a liquid metal is cast into a casting mold and solidification of the metal is induced by means of controlled cooling.
04/10/14
20140099198
Duct assembly
A duct for a gas turbine engine system is used to convey exhaust gas and bypass air away from the engine system, towards an exhaust nozzle. The duct includes an inlet face having at least two inlet portions and defines the outer extremity of a path for the gas and/or air through the duct.
04/10/14
20140099194
Bimetallic turbine shroud and method of fabricating
A bimetallic ring for use as a turbine shroud in a gas turbine engine. The bimetallic ring forms a sealing surface as a hot gas flow path boundary in the engine.
04/10/14
20140099190
Gas turbine engine turbine housing with enlongated holes
A turbine housing (430) includes a support housing (440) with an annular shape. The support housing (432) includes an outer surface (433) and an inner surface (434).
04/10/14
20140099189
Gas turbine engine components with lateral and forward sweep film cooling holes
An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The engine component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body.
04/10/14
20140099187
Oil baffle for gas turbine engine fan drive gear system
An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine, a compressor hub driven by the second shaft, the compressor hub within a compressor section of the gas turbine engine, an epicyclic gear train that is driven by the first shaft, and a common attachment point that secures the first shaft and the compressor hub to the second shaft.. .
04/10/14
20140099183
Turbine components with passive cooling pathways
The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface.
04/10/14
20140096827
Gas turbine engine with a multiple fuel delivery system
The present application provides a multiple fuel delivery system for use with a gas turbine engine. The multiple fuel delivery system may include a first fuel tank with a first fuel therein, a second fuel tank with a second fuel therein, a mixing chamber, and a flow divider downstream of the mixing chamber.
04/10/14
20140096537
Thin metal duct damper
A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the structural member, and a garter spring which abuts the first metal mesh pad.
04/10/14
20140096536
Bleed air slot
A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area.
04/10/14
20140096535
Gas turbine system with reheat spray control
The present application provides a gas turbine system. The gas turbine system may include a gas turbine engine producing a flow of exhaust gases, a heat recovery steam generator with a reheater and an evaporator in communication with the flow of exhaust gases, and a gas flow control system for diverting a first portion of the flow of exhaust gases away from the reheater and towards the evaporator..
04/10/14
20140096534
Low profile compressor bleed air-oil coolers
An air-oil cooler (aoc) for a gas turbine engine is disclosed. The aoc may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet.
04/10/14
20140096532
System and method for urea decomposition to ammonia in a side stream for selective catalytic reduction
A method for reducing nox emissions in the exhaust of a combined cycle gas turbine equipped with a heat recovery boiler and a catalyst effective for nox reduction, wherein a slip stream of hot flowing exhaust gases is withdrawn from the primary gas flow after the catalyst at a temperature of 500° f. To 900° f.
04/10/14
20140096531
Compressed air energy system integrated with gas turbine
An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (hp) and low pressure (lp) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the hp and lp air turbines.
04/10/14
20140096529
System and method for fuel and steam injection within a combustor
A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as o2 and o2 mixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor.
04/10/14
20140096528
Cooling for combustor liners with accelerating channels
A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner.
04/10/14
20140096527
Gas turbine engine combustor liner
A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and an effusion hole that communicates through the liner. .
04/10/14
20140096526
System for operating a combustor of a gas turbine
An end cover for a gas turbine combustor includes a main body configured to connect to a casing that at least partially surrounds a portion of the gas turbine. A fuel circuit extends within the main body of the end cover.
04/10/14
20140096523
Compressed air energy system integrated with gas turbine
An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (hp) and low pressure (lp) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the hp and lp air turbines.
04/10/14
20140096509
Geared turbofan engine with increased bypass ratio and compressor ratio ...
A gas turbine engine is typically comprised of a fan stage, multiple compressor stages, and multiple turbine stages. These stages are made up of alternating rotating blade rows and static vane rows.
04/10/14
20140096508
Systems and methods involving multiple torque paths for gas turbine engines
A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan.. .
04/10/14
20140096507
Bi-directional compression fan rotor for a gas turbine engine
A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades.
04/10/14
20140096504
Compressed air energy system integrated with gas turbine
An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (hp) and low pressure (lp) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the hp and lp air turbines.
04/10/14
20140096502
Burner for a gas turbine
A burner for a gas turbine is provided. The burner has a pilot combustor, a supply module providing pilot fuel and air into a pilot combustion room enclosed by a pilot burner housing having a tapered exit throat discharging radicals and heat generated in a pilot combustion zone into a main combustion room.
04/03/14
20140093392
Gas turbine engine component
Described is a gas turbine engine component (100), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.. .
04/03/14
20140093387
Method of manufacturing a cooled turbine blade with dense cooling fin array
A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins.
04/03/14
20140093379
Gas turbine engine component
A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.. .
04/03/14
20140093375
Reduced height ligaments to minimize non-integral vibrations in rotor blades
A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.. .
04/03/14
20140093370
Gas turbine engine combustor liner
A wrenching mechanism includes a multiple of rectilinear fastener plates each with a nut-shaped opening, each of the multiple of rectilinear fastener plates located within one of the multiple of rectilinear openings. A fastener mounted at least partially through the nut-shaped opening of each of the multiple of rectilinear fastener plates..
04/03/14
20140093368
Outer case with gusseted boss
An outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub.
04/03/14
20140093362
Gas turbine engine components and method of assembly
An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case.
04/03/14
20140093361
Airfoil with variable trip strip height
An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface.
04/03/14
20140093357
Gas turbine system and corresponding method for assembling
Method and gas turbine system having a reduced footprint. The gas turbine system includes a gas turbine configured to produce energy and having a gas turbine shaft; an auxiliary equipment attached to the gas turbine; an overhung shaft of the auxiliary equipment being configured to be attached to the gas turbine shaft; a flexible joint configured to be provided between the shaft of the auxiliary equipment and the gas turbine shaft; and a bearing system having at least two bearing units provided at a first end of the shaft of the auxiliary equipment next to the flexible joint.
04/03/14
20140093353
Solid seal with cooling pathways
The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough..
04/03/14
20140093350
Real time model based compressor control
A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series.


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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 patents 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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