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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 splitting

Rolls-royce Plc

Gas turbine splitting

Surface cooler support mechanism

Unison Industries

Surface cooler support mechanism

Surface cooler support mechanism

Gas turbine blade

Date/App# patent app List of recent Gas Turbine-related patents
05/21/15
20150142216
 Gas turbine engine turbine blade tip active clearance control system and method patent thumbnailnew patent Gas turbine engine turbine blade tip active clearance control system and method
A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud.
Honeywell International Inc.
05/21/15
20150142188
 Automated commissioning of a gas turbine combustion control system patent thumbnailnew patent Automated commissioning of a gas turbine combustion control system
Systems and methods for automating commissioning of a gas turbine combustion control system are provided. According to one embodiment of the disclosure, a system may include a controller and a processor communicatively coupled to the controller.
General Electric Company
05/21/15
20150139814
 Gas turbine blade patent thumbnailnew patent Gas turbine blade
A gas turbine blade 1 comprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surface 6a and a pressure-side cooling target surface 6b that face each other; and multiple vortex-generator-shaped fins 10 disposed between the two cooling target surfaces 6a and 6b such that the fins 10 connect the two cooling target surfaces 6a and 6b. Each of the vortex-generator-shaped fins 10 includes an oblique surface 33 located on the downstream side of the flow direction of a cooling medium.
05/21/15
20150139791
 Aircraft engine driveshaft vessel assembly and  assembling the same patent thumbnailnew patent Aircraft engine driveshaft vessel assembly and assembling the same
A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane.
General Electric Company
05/21/15
20150139789
 Array of flow-directing elements for a gas turbine compressor patent thumbnailnew patent Array of flow-directing elements for a gas turbine compressor
An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip..
Mtu Aero Engines Ag
05/21/15
20150139782
 Air separator for gas turbine engine patent thumbnailnew patent Air separator for gas turbine engine
An air separator in a gas turbine engine includes a cylindrical member and a seal flange having a flange body extending radially outward at a rearward end of the cylindrical member. A head portion is located at a radially outer free end of the flange body and includes an axial flange located axially rearward of the flange body and defining a rearward seal face for engagement with a blade disc forward face, and a forward cantilevered head mass extending axially forward from the flange body.
05/21/15
20150139779
 Gas turbine engine patent thumbnailnew patent Gas turbine engine
A fan containment system comprising an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener.
Rolls-royce Plc
05/21/15
20150139775
 System for extracting matter through variable bleed valves in turbines patent thumbnailnew patent System for extracting matter through variable bleed valves in turbines
A system for extracting foreign matter in a gas turbine includes multiple variable bleed valve (vbv) doors disposed on the outer engine casing between a low pressure compressor and a high pressure compressor for bleeding a portion of flow from a core engine flow path into a bypass flow path. The system includes an outlet guide vane (ogv) assembly having multiple guide vanes disposed within the core flow path and multiple support struts positioned downstream from the multiple guide vanes.
General Electric Company
05/21/15
20150136935
 Gas turbine engine stand patent thumbnailnew patent Gas turbine engine stand
A gas turbine engine stand (38) comprising an engine frame (48) and a base frame (46). The base frame (46) has a slide rail (51) to enable axial translation of the engine frame (48) relative to the base frame (46).
Rolls-royce Plc
05/21/15
20150136046
 Method for using the exhaust gases from plants for raw iron manufacture for generating steam patent thumbnailnew patent Method for using the exhaust gases from plants for raw iron manufacture for generating steam
A method and a system for generating steam using the waste gases from plants for pig iron manufacture: waste gas removed as export gas (12) from the plant for pig iron manufacture is thermally utilized by combustion, and the waste gas from the combustion is fed to a heat-recovery steam generator (29). To utilize more energy from the export gas (12) for power generation, the export gas (12) is fed into a combustion chamber (23) located upstream of the heat-recovery steam generator (29), and after the combustion in the heat-recovery steam generator (29), heat is extracted from the export gas (12) without the export gas (12) passing through a gas turbine between combustion and heat-recovery steam generator.
Siemens Vai Metals Technologies Gmbh
05/21/15
20150136043
new patent

Lng vaporization


Apparatus and methods for vaporizing lng while producing sufficient volume of compressed natural gas at sufficient pressure to meet the needs of internal combustion engines, gas turbines, or other high consumption devices operating on natural gas or on a mixture of diesel and natural gas. The lng vaporizer of the present invention incorporates a reciprocating pump to provide vaporized lng to an output at rates and pressures as required by the particular application.
05/21/15
20150135727
new patent

Automated water wash system for a gas turbine engine


The present application and the resultant patent provide a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a water wash system, and a system controller.
General Electric Company
05/21/15
20150135726
new patent

Surface cooler support mechanism


A surface heat exchanger is provided which utilizes forward and aft brackets to retain the heat exchanger in position. The surface heat exchanger includes a plurality of core cooling channels as well as fins which are disposed for air flow through the gas turbine engine.
Unison Industries, Llc
05/21/15
20150135722
new patent

System and controlling a two-shaft gas turbine


The control system includes a droplet spray device for spraying droplets to intake air for the compressor and a controller. The controller includes a fuel control section for adjusting a flow rate of the fuel to be supplied to the combustor, a spray flow rate control section for adjusting a flow rate of spray water to be supplied to the droplet spray device, an inlet guide vane aperture control section for adjusting the aperture of the inlet guide vane, and an efficiency improvement control section for outputting a command signal for bringing a balance between driving force for the compressor and power output of the high-pressure turbine to the fuel control section, the spray flow rate control section and the inlet guide aperture control section.
05/21/15
20150135719
new patent

Gas turbine combustor with tile having access hole for spark plug


The present invention relates to a gas-turbine combustion chamber with a combustion chamber wall, on which tiles are arranged, and with a recess for passing through an igniter plug, said recess extending through the combustion chamber wall and a tile, with the tile being provided with a tubular projection surrounding the recess and extending from that side of the tile facing away from a combustion chamber interior.. .
Rolls-royce Deutschland Ltd & Co. Kg
05/21/15
20150135717
new patent

Gas turbine combustor


A gas turbine combustor including a cluster-type burner is adapted to stabilize a combustion state by supplying a desired flow rate of combustion air to inner circumferential and outer circumferential fuel nozzle regions. A burner section of the combustor includes a plurality of fuel nozzles 2 and a premixing plate 4 in which are formed a plurality of premixing passages 3 each positioned at a downstream side of the corresponding one of the fuel nozzles 2, injected fuel from the plurality of fuel nozzles 2 being mixed with air in the premixing passage 3 before being supplied to a combustion chamber and burnt therein.
Mitsubishi Hitachi Power Systems, Ltd.
05/21/15
20150135716
new patent

Anti-coking liquid cartridge


A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.. .
General Electric Company
05/21/15
20150135715
new patent

Cooling system for gas turbine


A gas turbine comprises: a compressor 1 for compressing air; a combustor 2 for combusting the air compressed by the compressor 1 with fuel; and a turbine 3 driven by the combustion gas generated by the combustor 2, the turbine 3 including at least one turbine wheel 12a having turbine blades 11a on an outer circumferential section thereof. A gas turbine cooling system comprises a group of impingement cooling holes 32, provided in a partition wall 16a that separates the exit space 42 of the compressor 1 and the wheel space 43a located upstream of the turbine wheel 12a, for ejecting the compressed air 101 in the exit space 42 toward the turbine wheel 12a and the attachment portions of the turbine blades 11a..
05/21/15
20150135678
new patent

Gas turbine engine with noise attenuating variable area fan nozzle


A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path.
United Technologies Corporation
05/21/15
20150135659
new patent

Gas turbine filtration system with inlet filter orientation assembly


The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame.
Bha Altair, Llc
05/21/15
20150135535
new patent

Gas turbine splitting


A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44).
Rolls-royce Plc
05/14/15
20150134189

Systems and methods for remaining useful life predictions in drivetrains


Systems and methods for continually determining the remaining useful life of a drivetrain. The remaining useful life is continually determined during real-time operation of the drivetrain by determining a duty cycle based on torque and rotary speed measurements of the drivetrain.
05/14/15
20150132134

Injection molded composite fan platform


A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface.
05/14/15
20150132123

Gas turbine


A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1a) which is configured in a housing-side groove (3.1), a radially inner rim (1b) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (α) of at least 50° with the radially inner rim.. .
05/14/15
20150132122

Vane array with one or more non-integral platforms


A vane array adapted to be coupled to a vane carrier within a gas turbine engine is provided comprising: a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another; a u-ring; first connector structure for coupling a radially inner end section of each of the first and second airfoils to the u-ring; second connector structure for coupling a radially outer end section of each of the first and second airfoils to the vane carrier; a platform extending between the first and second airfoils; and platform connector structure for coupling the platform to one of the u-ring and the vane carrier.. .
05/14/15
20150132117

Gas turbine engine ducting arrangement having discrete insert


A ducting arrangement (10), including: a plurality of discrete ducts (18), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert (50) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.. .
05/14/15
20150132115

Unknown


A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (α) which increases in the flow direction (x).. .
05/14/15
20150132110

High durability turbine exhaust case


A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub.
05/14/15
20150132106

Gas turbine engine with low fan pressure ratio


A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.. .
05/14/15
20150132101

Cooling system with compressor bleed and ambient air for gas turbine engine


A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade.
05/14/15
20150129676

Compact actuation system for flow nozzle


Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions.
05/14/15
20150128613

Tapered thread and gas turbine


The object of the present invention is to reduce galling that occurs at a tapered thread according to generation of excessive pressure on a tip end side of the tapered thread. In order to attain the above-mentioned object, a tapered thread according to the present invention is characterized in that it is a tapered thread comprising a taper-shaped external thread threadedly engaged with a taper-shaped internal thread formed in a member that is to be fastened, a tapered thread center hole is formed in a bottom surface of the external thread, and a depth of the tapered thread center hole is not more than a half of an axial length of the external thread..
05/14/15
20150128609

Transition support system for combustion transition ducts for turbine engines


An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body.
05/14/15
20150128608

Gas turbine power plant with flue gas recirculation


A power plant including a gas turbine, a heat recovery boiler arrangement. The gas turbine includes a compressor inlet with a fresh air intake sector and an intake section for recirculated flue gas.
05/14/15
20150128607

Multi-swirler fuel/air mixer with centralized fuel injection


A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough.
05/14/15
20150128606

Combustion casing manifold for high pressure air delivery to a fuel nozzle pilot system


The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover.
05/14/15
20150128605

Turbofan with variable bypass flow


A gas turbine engine is disclosed with a bypass flow path having a bypass nozzle positioned downstream of a fan; a core flow path having a compressor, a combustor, a turbine and an exhaust nozzle; an auxiliary duct fluidly connecting the core flow path and the bypass flow path downstream of the turbine; and a control valve operably connected to the auxiliary duct to control fluid flow from the core flow path into the bypass flow path.. .
05/14/15
20150128604

Gas turbine engine flow path geometry


A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side.
05/14/15
20150128602

Heat shield for a gas turbine combustion chamber


The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.. .
05/14/15
20150128601

Gas turbine combustor


A gas turbine combustor having a burner including a plurality of fuel nozzles for injecting fuel, air hole plates positioned on a downstream side of the fuel nozzles and a plurality of air holes arranged in pairs with each of the fuel nozzles, and a combustion chamber for mixing fuel injected from the fuel nozzles and air injected from the air holes and injecting and burning the mixed fuel. Each of the fuel nozzles configuring the burners is provided with a projection in which a part of an outer edge of a section of the fuel nozzle is protruded outward; and the projection is arranged so as to be directed toward a center of the gas turbine combustor.
05/14/15
20150128599

Continuous detonation combustion engine and system


One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system.
05/14/15
20150128598

Cooling air temperature reduction using nozzles


A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas.
05/14/15
20150128561

Three stream, variable area, vectorable nozzle


An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine.
05/14/15
20150128559

Advanced humid air gas turbine system


The ahat includes a gas turbine system; a heat recovery steam generator for generating steam by use of exhaust gas from a turbine; a water recovery system for recovering moisture contained in the exhaust gas; a first steam system for supplying steam, coming from the heat recovery steam generator, to a compressed air header; and a second steam system for supplying steam, coming from the heat recovery steam generator, to the heat recovery steam generator or the water recovery system. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine.
05/14/15
20150128540

Gas turbine filter and methods of assembling same


Systems and methods are provided for a filter system with an internal support structure. An embodiment of the filter system includes a header frame, a support structure having at least one arm, and a filter unit having at least one pocket.
05/07/15
20150125310

Gas turbine airfoil


A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction.
Mitsubishi Hitachi Power Systems, Ltd.
05/07/15
20150125308

Manufacture of filled aerofoil


A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position.
Rolls-royce Plc
05/07/15
20150125305

Low profile fan platform attachment


A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug..
United Technologies Corporation
05/07/15
20150125304

Mass offset for damping performance


A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface.
United Technologies Corporation
05/07/15
20150125301

Platform seal strip, turbine blade assembly and assembling it


A platform seal strip, in particular for use in a gas turbine blade assembly, is provided. The platform seal strip includes an upper side, a lower side, a first portion and a second portion.
Siemens Aktiengesellschaft
05/07/15
20150125286

Atr axial v-groove


A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125285

Integrated nozzle and plug


A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125284

Atr full ring sliding nacelle


A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core.
United Technologies Corporation
05/07/15
20150125282

Braze alloy compositions and brazing methods for superalloys


A multi-component braze filler alloy comprising 60-70% by weight cm247 superalloy and brb braze alloy is diffusion brazed to a cm247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface.
05/07/15
20150125281

Braze alloy compositions and brazing methods for superalloys


A multi-component braze filler alloy comprising at least 70% by weight marm509a superalloy with the remainder marm509b superalloy is diffusion brazed to a cm247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service..
05/07/15
20150125270

Atr guide pins for sliding nacelle


A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125267

Standardized gas turbine inspection port system


A standardized inspection port system with common inspection port bodies and port plugs are incorporated in plural inspection locations within a gas turbine engine casing to facilitate internal engine inspection. The inspection ports preferably have identical internal diameter, stub flange dimensions and axial length from the gas turbine casing inspection seat to the stub flange for standardized mounting of inspection instruments at different locations about the turbine.
05/07/15
20150125264

Gas turbine engine lubrication system


A lubrication system for a gas turbine engine is disclosed. The lubrication system is configured to provide pressurized air and lubricant to a bearing sump of the gas turbine engine to cool and lubricate a bearing included in the bearing sump..
Rolls-royce Corporation
05/07/15
20150125259

Gas turbine engine variable pitch fan blade


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section.
United Technologies Corporation


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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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