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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
04/10/14
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 patent thumbnailMethod 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 patent thumbnailSystem 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 patent thumbnailGas 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 patent thumbnailDuct 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 patent thumbnailBimetallic 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 patent thumbnailGas 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 patent thumbnailGas 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 patent thumbnailOil 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 patent thumbnailTurbine 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 patent thumbnailGas 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.
04/03/14
20140091577
Air separation power generation integration
The present invention provides a method and apparatus for separating air and generating electrical power. A compressed air stream produced in a main air compressor is introduced into an air separation unit that cryogenically rectifies the air into component products.
04/03/14
20140091531
Spline seal with cooling pathways
The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path..
04/03/14
20140090930
Multiple reservoir lubrication system
A lubrication system for use with a gas turbine engine includes a first reservoir for containing a lubricant. The first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction.
04/03/14
20140090492
Embedded cap probe
A method for installing a probe assembly in a case of a gas turbine engine is disclosed. The method may include installing a first portion of the probe assembly within a first section of the case, and installing a second portion of the probe assembly within a second section of the case.
04/03/14
20140090456
Model based engine inlet condition estimation
A gas turbine engine inlet sensor fault detection and accommodation system comprises an engine model, an engine parameter comparison block, an inlet condition estimator, control laws, and a fault detection and accommodation system. The engine model is configured to produce a real-time model-based estimate of engine parameters.
04/03/14
20140090400
Variable flow divider mechanism for a multi-stage combustor
The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage combustion.
04/03/14
20140090397
Bleed tube attachment
An anti-vortex assembly for a gas turbine engine includes a support ring including a seat surrounding an opening and a bleed tube including a base with a bearing face sealing against the seat. A retaining ring is mounted within the support ring and engages the base of the bleed air tube to hold the bleed tube within the support ring..
04/03/14
20140090396
Combustor with radially staged premixed pilot for improved
The present invention discloses a novel apparatus and method for a mixing fuel and air in a gas turbine combustion system. The mixer helps to mix fuel and air while being able to selectively increase the fuel flow to a shear to a shear layer of a pilot flame in order to reduce polluting emissions.
04/03/14
20140090395
Gas turbine engine
A cooling system for a gas turbine engine (10). The system is comprises a fuel air heat exchanger (78) comprising a fuel passage (80) in thermal contact with an engine cooling air passage (82).
04/03/14
20140090392
Model based fuel-air ratio 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.
04/03/14
20140090391
Combuster with radial fuel injection
A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system.. .
04/03/14
20140090390
Flamesheet combustor dome
The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture..
04/03/14
20140090389
Variable length combustor dome extension for improved operability
The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures..
04/03/14
20140090388
Off-take power ratio
An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement of a gas turbine engine; and driving the spool of the gas turbine engine using a second amount of power, wherein a ratio of the first amount of power to the second amount of power is greater than or equal to 0.009.. .
04/03/14
20140090386
Geared turbofan with fan and core mounted accessory gearboxes
A disclosed accessory drive system provides for the reduction in the overall diameter of the outer nacelle by splitting the number of accessory components between a first gear box mounted within the outer nacelle and a second gearbox mounted to the core engine. The first gear box mounted to the fan case of the gas turbine engine drives a first plurality of accessory components.
04/03/14
20140090384
Gas turbine engine cooling hole with circular exit geometry
A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape.
04/03/14
20140090376
Organic rankine cycle for mechanical drive applications
A combined thermodynamic system for the production of mechanical power. The system comprises a gas turbine and a turbomachinery driven by the gas turbine.
04/03/14
20140090356
Heat recovery steam generator and power plant
A heat recovery steam generator has a plurality of heat exchangers, including superheaters 28, 30, an evaporator 32 and an economizer 34, disposed in a duct 27 along the flow direction of an exhaust gas 25 from a gas turbine 14, and generates steam by utilizing the exhaust gas 25 from the gas turbine 14. The heat recovery steam generator includes: auxiliary combustors 50, 52, each disposed upstream of one of the heat exchangers, for heating the exhaust gas by means of burners; and an air supply device for supplying air to the burners of the auxiliary combustor 52 from the outside of the duct..
04/03/14
20140090355
Reduced trim flow gas turbine engine oil system
A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity..
04/03/14
20140090353
Systems and methods for determining a target exhaust temperature for a gas turbine
Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine.


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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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