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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


Rotor device, turbine rotor device, and gas turbine and turbine engine having same

Rotor device, turbine rotor device, and gas turbine and turbine engine having same

Turbine split ring retention and anti-rotation method

Turbine split ring retention and anti-rotation method

Turbine split ring retention and anti-rotation method

Guide vane arrangement

Date/App# patent app List of recent Gas Turbine-related patents
10/09/14
20140301861
 Airfoil having an erosion-resistant coating thereon patent thumbnailAirfoil having an erosion-resistant coating thereon
A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose.
10/09/14
20140301858
 Rotor device, turbine rotor device, and gas turbine and turbine engine having same patent thumbnailRotor device, turbine rotor device, and gas turbine and turbine engine having same
Disclosed is a turbine rotor device for a gas turbine, the turbine rotor device comprising a turbine rotor body, and a pre-stressed fiber-wound layer, wherein the pre-stressed fiber-wound layer is wound on the periphery of the turbine rotor body to exert a predetermined pre-loading force on the turbine rotor body. Additionally, a rotor, and a gas turbine and a turbine engine having the turbine rotor device are also provided..
10/09/14
20140301849
 Turbine split ring retention and anti-rotation method patent thumbnailTurbine split ring retention and anti-rotation method
A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate.
10/09/14
20140301840
 Guide vane arrangement patent thumbnailGuide vane arrangement
A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward.
10/09/14
20140301838
 Repair of a gas turbine component patent thumbnailRepair of a gas turbine component
A gas turbine component is provided having a repaired vane platform and rail region in which a portion of the vane rail having been damaged during operation is removed. A bar insert is rough machined and is secured within a groove in the rail.
10/09/14
20140301834
 Turbine cylinder cavity heated recirculation system patent thumbnailTurbine cylinder cavity heated recirculation system
A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system.
10/09/14
20140301820
 Turbine engine shutdown temperature control system with nozzle injection for a gas turbine engine patent thumbnailTurbine engine shutdown temperature control system with nozzle injection for a gas turbine engine
A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine.
10/09/14
20140299581
 Method for welding rotors for power generation patent thumbnailMethod for welding rotors for power generation
The invention relates to a method for welding rotors for power generation such as gas turbines, steam turbines, and generators having a plurality of rotor discs arranged along a rotor axis. The method includes providing said discs with a weld seam preparation.
10/09/14
20140298821
 Gas turbine engine provided with heat exchanger, and method for starting same patent thumbnailGas turbine engine provided with heat exchanger, and method for starting same
A method of starting a gas turbine engine includes a primary warming step of warming a heat exchanger (6) by means of a compressed gas (g1) while with the use of an inverter motor (im) the rotation speed of the engine is maintained at a partial rotation speed, a secondary warming step of warming the heat exchanger (6) by activating a main combustor (2) to gradually increase the temperature of an exhaust gas (g3) while with the use of the inverter motor (im) the rotation speed is maintained at the partial rotation speed, and a speed increasing step of increasing the rotation speed to the rated rotation speed with the use of the inverter motor (im) while the fuel burning amount of the main combustor (2) is increased.. .
10/09/14
20140298820
 Gas turbine engine and method for starting same patent thumbnailGas turbine engine and method for starting same
A starting method for a gas turbine engine includes a primary warming step of warming up the gas turbine engine while a constant primary warm-up rotation speed is maintained by an inverter motor and a secondary warming step of warming up the gas turbine engine while a constant secondary warm-up rotation speed is maintained by further increasing the speed of the inverter motor. The primary warming step terminates when an electric power required by the inverter motor attains a predetermined preset electric power value.
10/09/14
20140298818
Control method and control device for lean fuel intake gas turbine
A method and a device for controlling a lean fuel intake gas turbine engine, which can stably maintain operation of the gas turbine engine by preventing misfire and burnout of a catalytic combustor even when a catalyst in the combustor is deteriorated. A difference between measured temperatures of an inlet and an outlet of the combustor with respect to a methane concentration in an intake gas that is to be taken into the lean fuel intake gas turbine engine is compared with reference temperature difference data that is data indicating difference between temperatures of the inlet and the outlet of the combustor including a catalyst in its initial state to be a reference, and at least one of the inlet temperature and the outlet temperature of the combustor is controlled based on a difference between the measured temperature difference and the reference temperature difference data..
10/09/14
20140298817
Arrangement for preparation of liquid fuel for combustion and a method of preparing liquid fuel for combustion
A preparation of liquid fuel for combustion, particularly for ignition, in the burners of a gas turbine is proposed. A source of heated liquid fuel, particularly heated pressurized fuel, is arranged in a reservoir.
10/09/14
20140298815
Repairing method of plate member, plate member, combustor, ring segment, and gas turbine
A repair method of a plate member disposed so as to separate a high-pressure space and a low-pressure space and having a cooling passage provided inside thereof along a surface thereof, comprising: removing a damaged portion generated in the plate member so as to expose the cooling passage; primarily filling an area where a material is removed so as to block the cooling passage and form an external shape of the plate member having no missing portion as compared to its original external shape; forming a first opening through which the cooling passage communicates with the low-pressure space on an upstream side, in a flow direction of a refrigerant in the cooling passage, of a position where the cooling passage is blocked; and forming a second opening through which the cooling passage communicates with the high-pressure space on a downstream side of the position where the cooling passage is blocked.. .
10/09/14
20140298788
Gas turbine engine including pneumatic actuator system
A gas turbine engine that includes a compressor section and a pneumatic actuator system is delivered. The pneumatic actuator system includes a bleed air duct that receives bleed air from the compressor section and delivers the bleed air through an accumulator and to an actuator.
10/09/14
20140298771
Gas turbine exhaust diffuser
A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet.
10/02/14
20140297155
Aircraft power outtake management
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power.
10/02/14
20140294598
Turbine blade
The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.. .
10/02/14
20140294589
Asymmetrically slotted rotor for a gas turbine engine
A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path..
10/02/14
20140294581
Gas turbine engine access panel
An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. In one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade.
10/02/14
20140294579
Composite guide vane
A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing.
10/02/14
20140294572
Wall section for the working gas annulus of a gas turbine engine
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294571
Seal segment
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294564
Auxiliary power units and other turbomachines having ported impeller shroud recirculation systems
Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system.
10/02/14
20140294562
Strut for a gas turbine engine
The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut..
10/02/14
20140294560
Gas turbine shroud assemblies
Embodiments of the present disclosure include a gas turbine shroud assembly. The shroud assembly may include a shroud structure that defines a first cooling chamber and a second cooling chamber.
10/02/14
20140294559
Multiple mode gas turbine engine gas fuel system with integrated control
A method for operating a gas turbine engine is disclosed. The method includes determining whether the gas turbine engine fuel system is in a steady state mode or a transient mode.
10/02/14
20140291993
Method for operating lean fuel intake gas turbine engine, and gas turbine power generation device
A method for stably operating a lean fuel intake gas turbine engine by controlling the rotation speed of the lean fuel intake gas turbine engine for which it is difficult to control the rotation speed by controlling a fuel flow rate, is provided. In a method for operating a lean fuel intake gas turbine engine (gt) configured to use, as a fuel, a combustible component contained in a low-concentration methane gas to drive a power generator, a power converter (17) is provided between an external electric power system (19) and the power generator (11), and a rotation speed of the power generator (11) is controlled by the power converter (17), to control a rotation speed of the gas turbine engine (gt)..
10/02/14
20140290911
Intake air cooling system
An intake air cooling system 100 for a gas turbine 18 is provided with: an intake duct 12 for leading intake air taken in from an intake-air inlet 22 to a compressor 14 of the gas turbine; a cooling part provided in the intake duct and configured to cool the intake air by heat exchange with a cooling medium which is introduced from an outside; a protruding step part 13 formed in a convex shape protruding from bottom surfaces 12a1, 12a2 of the intake duct disposed on a downstream side of the cooling part; and at least one drain hole 110 formed in the bottom surfaces 12a1, 12a2 of the intake duct disposed on the downstream side of the cooling part so as to discharge drain water, generated on a surface of the cooling part and dropping from the surface, to an outside of the intake duct.. .
10/02/14
20140290910
Intake air cooling system
An intake air cooling system 100 for a gas turbine 18 is provided with: an intake duct 12 for leading intake air taken in from an intake-air inlet 22 to a compressor 14 of the gas turbine 18; a cooling part 26 provided in the intake duct to cool the intake air by heat exchange with a cooling medium introduced from an outside; a drain discharge line 102 connected to a part of the intake duct below an inlet 14a of the compressor so as to discharge drain water flowing along an inner peripheral surface of the intake duct; and a water seal part 104 provided in the drain discharge line 102 to keep water seal in a part of the drain discharge line 102 by a water pressure at least corresponding to an amount of a negative pressure in the vicinity of the inlet of the compressor.. .
10/02/14
20140290272
Gas turbine engine cooling arrangement
A gas turbine engine comprises a compressor, a combustion chamber, an outer casing, an inner casing and a cooling arrangement. The outer casing surrounds the compressor and the combustion chamber and the combustion chamber has turbine nozzle guide vanes.
10/02/14
20140290271
Mounting arrangement
A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness.
10/02/14
20140290269
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.. .
10/02/14
20140290268
Gas turbine engine geared architecture axial retention arrangement
A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed..
10/02/14
20140290266
Fuel and actuation system for gas turbine engine
A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit.
10/02/14
20140290265
Gas turbine engine with transmission
A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g.
10/02/14
20140290264
Control of the gas composition in a gas turbine power plant with flue gas recirculation
The invention relates to a method for operating a gas turbine power plant with exhaust gas recirculation. In the method a setpoint concentration of one component of the inlet gas and/or of the hot working gas and/or of the exhaust gas of the gas turbine is determined in a first step, in accordance with the operating conditions of the gas turbine, from a combination of a setpoint value of a control loop, a feedforward control signal and a correction value.
10/02/14
20140290262
Low flow correction for gas turbine engine fuel valve characteristics
A method for controlling a gas turbine engine fuel control valve during low flow conditions includes positioning the fuel control valve in an operating position. The method also includes determining a fuel control valve flow sensor flow rate while in the operating position and determining a corrected effective flow area (“cda”) of the fuel control valve.
10/02/14
20140290261
Compensation for gas turbine engine fuel valve characteristics
A method for operating a gas turbine engine fuel system with a fuel control valve is disclosed. The method includes metering fuel through the fuel control valve with an effective flow area versus command data set.
10/02/14
20140290260
System and method for generating nitrogen from a gas turbine
A system includes a gas turbine. The gas turbine includes a first compressor configured to provide a first portion of a discharge air to a combustor.
10/02/14
20140290258
Method for the arrangement of impingement cooling holes and effusion holes in a combustion chamber wall of a gas turbine
A method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall including: distribution of the effusion holes in the surface to be cooled in accordance with pattern, diameter and dimension selections made; distribution of the impingement cooling holes in accordance with pattern, diameter and dimension selections made; checking of the number of matches and their spacing from one another, taking into account the component and assembly tolerances; comparison with the permitted number and their minimum spacing; and, if quality requirements are not met, taking corrective actions, including selecting alternative diameters and patterns.. .
10/02/14
20140290255
Hollow curved plate, manufacturing method of the same and combustor of gas turbine
Hollow curved plates (20, 50, 70) include first plate members 241-243 having a first groove 22 and second plate members 341-343 having a second groove 32 of approximately the same width as the first groove 22, the second plate members 341-343 being bonded to the first plate members 241-243 by diffusion bonding. The hollow curved plate is formed of the first plate members 241-243 and the second plate members 341-343 curved by bending in a state where the first plate members 241-243 and the second plate members 341-343 are bonded together.
10/02/14
20140290254
Cyclonic dirt separating turbine accelerator
A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.. .
10/02/14
20140290253
Intake air cooling system
An intake air cooling system 100 for a gas turbine 18 is provided with: an intake duct 12 for leading intake air from an intake-air inlet 22 to a compressor 14 of the gas turbine, the intake duct having a vertical duct 12c and a manifold part 12d disposed on a downstream side of the vertical duct; a cooling part 26 provided in the intake duct to cool the intake air by heat exchange with a cooling medium which is introduced from an outside; a filter part 42 provided on an inlet side of the manifold part to remove impurities contained in the intake air introduced through the vertical duct; and a drain catcher 110 constituted by a gutter member provided immediately above the filter part along inner wall surfaces 12c1, 12c2 of the vertical duct, the drain catcher being configured to collect drain water flowing along the inner wall surfaces of the vertical duct.. .
10/02/14
20140290252
Gas turbine engine provided with scroll
A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other.
10/02/14
20140290213
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.. .
10/02/14
20140290209
Gas turbine apparatus
A gas turbine apparatus may include one or more driving shafts; a compressor configured to receive power from the one or more driving shafts, suck air, and compress the sucked air at high pressure. The gas turbine may include a combustor configured to mix the compressed air with fuel, and combust the fuel mixture to generate combustion gas.


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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