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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


Systems and methods to control variable stator vanes in gas turbine engines

Gas turbine engine shaft bearing configuration

Gas turbine engine mid turbine frame with flow turning features

Date/App# patent app List of recent Gas Turbine-related patents
07/24/14
20140206496
 Method of assembly for gas turbine fan drive gear system patent thumbnailnew patent Method of assembly for gas turbine fan drive gear system
A method of assembling an epicyclic gear train comprises the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures.
07/24/14
20140205449
 Superalloys and components formed thereof patent thumbnailnew patent Superalloys and components formed thereof
A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine.
07/24/14
20140205448
 Exhaust diffuser and method for manufacturing an exhaust diffuser patent thumbnailnew patent Exhaust diffuser and method for manufacturing an exhaust diffuser
An exhaust diffuser and method for manufacturing an exhaust diffuser is provided. An exhaust diffuser for a torque-generating turbine, in particular a torque-generating gas turbine is provided herein.
07/24/14
20140205447
 Purge and cooling air for an exhaust section of a gas turbine assembly patent thumbnailnew patent Purge and cooling air for an exhaust section of a gas turbine assembly
A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls.
07/24/14
20140205445
 Gas turbine patent thumbnailnew patent Gas turbine
A gas turbine includes a disk wheel forming a rotor; a rotor blade including a shank mounted on the outer circumference of the disk wheel and a rotor blade profile portion; a stator blade including a stator blade profile portion and an inner circumferential end wall provided on the inner circumferential side of the stator blade profile portion; and a seal fin provided on the shank of the rotor blade so as to face an inside-diameter surface of the inner circumferential end wall of the stator blade. An abradable coating is applied to such a portion of the inside-diameter surface of the inner circumferential end wall of the stator blade that faces the seal fin..
07/24/14
20140205443
 Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine patent thumbnailnew patent Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane the grooves are arranged such that a circumferential space is defined between adjacent grooves during operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path..
07/24/14
20140205441
 Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine patent thumbnailnew patent Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface.
07/24/14
20140205439
 Gas turbine engine shaft bearing configuration patent thumbnailnew patent Gas turbine engine shaft bearing configuration
A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case.
07/24/14
20140205438
 Relationship between fan and primary exhaust stream velocities in a geared gas turbine engine patent thumbnailnew patent Relationship between fan and primary exhaust stream velocities in a geared gas turbine engine
An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an exhaust velocity ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90..
07/24/14
20140205424
 Systems and methods to control variable stator vanes in gas turbine engines patent thumbnailnew patent Systems and methods to control variable stator vanes in gas turbine engines
Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring.
07/24/14
20140203557
new patent System and method for extending minimum turn down load of combined cycle power plant
A system including a gas turbine system and an electrolysis unit configured to produce a hydrogen gas for reducing a minimum emissions compliance load of the gas turbine system.. .
07/24/14
20140202253
new patent Optical sensor
An optical sensor is disclosed for measuring pressure and/or temperature. The optical sensor is adapted for use in high temperature environments, such as gas turbines and other engines.
07/24/14
20140202186
new patent Zoned evaporative cooling media for air intake house of gas turbine
An evaporative cooling system for combustion gas turbine system has an array of cooling media including first and second cooling media types. The first cooling media type has a first maximum air velocity rating, and the second cooling media type has a second maximum air velocity rating that greater than the first maximum air velocity rating..
07/24/14
20140202167
new patent Power generation system
The power generation system includes a fuel cell that generates electric power using a fuel gas, a gas turbine including an air compressor, a combustor, and a turbine, an exhaust fuel line that introduces an exhaust fuel gas discharged from the fuel cell into the combustor, a branch exhaust fuel line branching off midway from the exhaust fuel line, a switching unit that sends the exhaust fuel gas to one of the branch exhaust fuel line and the combustor, and a heating portion that heats the exhaust fuel line at a downstream side of the switching unit.. .
07/24/14
20140202166
new patent Method of operating a gas turbine for reduced ammonia slip
Described herein are methods of operating a gas turbine engine (12) for reduced ammonia slip. An exemplary method (100) includes operating (102) the engine over a range of power output levels; controlling (104) a mass flow of nox produced in exhaust (19) of the engine to be within 10% over the range of power output levels; and treating (106) the exhaust of the engine in a selective catalytic reduction process (22).
07/24/14
20140202164
new patent Gas turbine engine nozzle including housing having scalloped root regions
A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons.
07/24/14
20140202162
new patent Fuel efficient ultra-low emission and improved pattern factor colorless distributed combustion for stationary and propulsion gas turbine applications
Colorless distributed combustion (cdc) reactors or green combustion gas turbine combustors having a combustion chamber are presented for improved performance of gas turbine combustion engines. The combustors are configured and designed for providing a superior pattern factor (uniform thermal field in the combustion zone) and a reduction or complete elimination of pollutants emission from the combustor (i.e., zero emission gas turbine combustor) and uniform thermal field in the entire combustion zone to provide significantly improved pattern factor.
07/24/14
20140202160
new patent Gas turbine system with manifold
A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.. .
07/24/14
20140202158
new patent Gas turbine engine heat exchangers and methods of assembling the same
A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel.
07/24/14
20140202157
new patent Thermal energy storage for combined cycle power plants
Thermal storage systems that preferably do not create substantially any additional back pressure or create minimal additional back pressure and their applications in combined cycle power plants are disclosed. In one embodiment of the method for efficient response to load variations in a combined cycle power plant, the method includes providing, through a thermal storage tank, a flow path for fluid exiting a gas turbine, placing in the flow path a storage medium comprising high thermal conductivity heat resistance media, preferably particles, the particles being in contact with each other and defining voids between the particles in order to facilitate flow of the fluid in a predetermined direction constituting a longitudinal direction, arrangement of the particles constituting a packed bed, dimensions of the particles and of the packed bed being selected such that a resultant back pressure to the gas turbine is at most a predetermined back pressure..
07/24/14
20140202155
new patent Solar thermal electric power generation system
A solar thermal electric power generation system using heating medium that undergoes phase change between liquid phase and vapor phase, including a fresnel type heat collectors for heating the heating medium by solar thermal energy, a gas turbine generating device for generating electric power while discharging exhaust gas, a heating device including a first channel through which the heating medium flows and a second channel which is located near the first channel and through which the exhaust gas from the gas turbine generating device flows, a vapor-liquid separating device for separating the heating medium having been heated by the heating device into vapor phase and liquid phase, and a turbine generating device driven by the heating medium in vapor phase separated by the vapor-liquid separating device. The heating device heats the heating medium in the first channel by the exhaust gas in the second channel..
07/24/14
20140202133
new patent Gas turbine engine mid turbine frame with flow turning features
A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage.
07/17/14
20140200721
Stabilizing a gas turbine engine via incremental tuning during transients
Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored.
07/17/14
20140199176
Gas turbine engine nose cone attachment configuration
A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub.
07/17/14
20140199175
Gas turbine engine components and methods for their manufacture using additive manufacturing techniques
In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3d design model for the component, adding one or more crack resistant features to the 3d design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component..
07/17/14
20140199163
Abradable layer including a low thermal conductivity composition
A system may include a blade track or blade shroud and a gas turbine blade that includes a blade tip. The blade track or blade shroud may include a substrate and an abradable layer formed over the substrate.
07/17/14
20140196473
Geared turbofan gas turbine engine architecture
A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
07/17/14
20140196472
Geared turbofan gas turbine engine architecture
A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
07/17/14
20140196471
Fan drive gear system flexible support features
A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case.
07/17/14
20140196470
Gas turbine engine buffer system
A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure..
07/17/14
20140196469
Low pressure compressor bleed exit for an aircraft pressurization system
An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level.. .
07/17/14
20140196467
Oxidizing fuel
A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system.
07/17/14
20140196466
Methods and systems for operating gas turbine engines
Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation.
07/17/14
20140196465
Lean-rich axial stage combustion in a can-annular gas turbine engine
An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16).
07/17/14
20140196464
System and method for protecting components in a gas turbine engine with exhaust gas recirculation
A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section..
07/17/14
20140196463
High efficiency, high pressure gas turbine engine fuel supply system and method
A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition.
07/17/14
20140196459
High pressure, multiple metering zone gas turbine engine fuel supply system and method
A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition.
07/17/14
20140196458
Damping device and gas turbine combustor
In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space b by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces da and db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts ea and eb of a predetermined length by partitioning the resonance spaces da and db..
07/17/14
20140196437
Method for operating a static gas turbine, and intake duct for intake air of a gas turbine
An ambient air intake duct of a static gas turbine is provided, having at least one filter, which is arranged in the intake duct, for cleaning the ambient air (a) that can flow through the intake duct. A method for operating a static gas turbine which is equipped with a filter for cleaning the ambient air (a) is also provided.
07/17/14
20140196433
Gas turbine engine component platform cooling
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform..
07/10/14
20140193761
Rail cars for transporting heavy hydrocarbons
A method and system of temperature control of heavy hydrocarbons in a consist of rail cars is disclosed wherein waste heat from one or more of the locomotives propelling the train is utilized to heat the heavy hydrocarbons in a consist or ambient air is used to cool the heavy hydrocarbon cargo. The train is typically comprised of tanker cars that can be filled with raw heavy hydrocarbon, not dilbit thus allowing about 20% to about 30% additional heavy hydrocarbon to be transported in each tanker car.
07/10/14
20140193274
Fuel-cooled bladed rotor of a gas turbine engine
Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade.
07/10/14
20140193272
Gas turbine engine cooling systems and methods incorporating one or more cover plate assemblies having one or more apertures therein
Turbine cooling systems and methods are disclosed herein. The turbine cooling system may include a rotor disk having a bucket attached thereto.
07/10/14
20140193252
Gas turbine half-casing lifting and shipping fixture
A lifting fixture assembly adapted for shipping and/or lifting includes a lower turbine casing having two horizontal joint flanges adapted to engage mating flanges on an upper-turbine casing. The horizontal joint flanges are provided with plural bolt holes used for securing the upper turbine casing to the lower turbine casing.
07/10/14
20140193251
Stator anti-rotation device
A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case. An anti-rotation plate extends from a flange of the case between adjacent ones of the plurality of vanes for preventing rotation of the plurality of vanes relative to the case..
07/10/14
20140193249
Electrical conductor paths
A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally.. .
07/10/14
20140193246
Cooling hole with crenellation features
A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region..
07/10/14
20140193241
Internally coolable component for a gas turbine with at least one cooling duct
An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators..
07/10/14
20140193238
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 that is rotatable about an axis. A speed reduction device is connected to the fan.


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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