Follow us on Twitter
twitter icon@FreshPatents


Gas Turbine patents

      

This page is updated frequently with new Gas Turbine-related patent applications.




 Device for mounting a spark plug in a combustion engine of a gas turbine engine patent thumbnailnew patent Device for mounting a spark plug in a combustion engine of a gas turbine engine
A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards.
Snecma


 Burner, gas turbine having such a burner, and fuel nozzle patent thumbnailnew patent Burner, gas turbine having such a burner, and fuel nozzle
A burner having a plurality of pre-mixing chambers each having a fuel nozzle for two fuels, the fuel nozzle has a fuel lance extending in a flow direction, in which fuel lance first outlet openings for a first fuel are introduced. The fuel lance is surrounded by an outer pipe having at least one second outlet opening for a second fuel, the first outlet openings oriented radially and the second outlet opening oriented axially, a flow cross-section is formed between the fuel lance and the inside of the pre-mixing chamber and vortex generators are arranged on the fuel lance.
Siemens Aktiengesellschaft


 Cylinder for combustor, combustor, and gas turbine patent thumbnailnew patent Cylinder for combustor, combustor, and gas turbine
A cylinder for a combustor provided with a cylindrical member, a first cooling passage and a second cooling passage formed in the cylindrical member, and a supply port extended portion. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member.
Mitsubishi Hitachi Power Systems, Ltd.


 Combustor for a gas turbine engine patent thumbnailnew patent Combustor for a gas turbine engine
In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel.
Rolls-royce Plc


 Combustor, gas turbine provided with same, and  repairing combustor patent thumbnailnew patent Combustor, gas turbine provided with same, and repairing combustor
A combustor is provided with a combustion liner (12) in which a combustion gas flows through the inner peripheral side and a plurality of through-holes (14) are formed, and a sound attenuator (20) having a space-forming member (21) configured to form a space (s) connected to the plurality of through-holes (14) at the outer peripheral side of the combustion liner (12). A method of repairing a combustor involves executing: an opening step of opening a portion of the space-forming member (21) in contact with the outside and bringing the outside and the space (s) in communication with each other; a cylinder repair step of repairing the combustion liner (12); a foreign substance removal step of removing foreign substances in the space (s) from the opening (23) opened in the opening step to the outside, after the cylinder repair step; and a closing step of closing the opening (23) using a lid (24), after the foreign substance removal step..
Mitsubishi Hitachi Power Systems, Ltd.


 Planet gearbox with cylindrical roller bearing with under race lube scheme patent thumbnailnew patent Planet gearbox with cylindrical roller bearing with under race lube scheme
A planet gear rotatable on a planet bearing with cylindrical rollers is mounted to a carrier of an epicyclic gearing arrangement. Either the cylindrical outer surface of the support pin or the opposing cylindrical inner surface of the inner ring of the planet bearing includes a network of interconnected grooves.
General Electric Company


 Geared gas turbine engine patent thumbnailnew patent Geared gas turbine engine
A gas turbine engine includes gearbox including sun gear, annulus gear, plurality of planet gears and carrier. Each planet gear is rotatably mounted in carrier by bearing.
Rolls-royce Plc


 Assembly for the rotatably fixed connection of at least two rotating parts in a gas turbine and balancing method patent thumbnailnew patent Assembly for the rotatably fixed connection of at least two rotating parts in a gas turbine and balancing method
The fastening element is additionally equipped and intended to fix at least one balancing element on the holding element.. .

 Compressor patent thumbnailnew patent Compressor
A compressor section for a gas turbine engine, the compressor section including a circumferential row of stator vanes, a circumferential row of rotor blades, and a casing arrangement. A row of bleed ports are provided in the casing arrangement.
Rolls-royce Plc


 Reduced stress rotor interface patent thumbnailnew patent Reduced stress rotor interface
A bladed rotor and a hub rotor for a gas turbine are provided. A bladed rotor may comprise a rotor interface comprising a radially inward surface, wherein the rotor interface comprises a constant diameter zone; and a reduced stress zone located adjacent to and aft of the constant diameter zone.
United Technologies Corporation


new patent

Thrust scheduling variable pitch fan engines and turbo-shaft, turbo-propeller engines

A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor; receiving a control command from a full authority digital engine control (fadec) in the control system; generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received; generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; and supplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine..
General Electric Company

new patent

Systems and methods for injection of bio-diesel into a gas turbine combustor

Certain embodiments may include systems and methods that comprise a first unit controller associated with a first gas turbine and a second unit controller associated with a second gas turbine. A first unit human machine interface is coupled to the first unit controller and is operable to provide first blend information to the first unit controller.
General Electric Company

new patent

Variable power limit control for gas turbines

A method for operating a gas turbine plant having a gas turbine and an electric generator driven by the gas turbine. The method includes detecting an instantaneous power of the gas turbine plant; comparing the detected instantaneous power with a power limit value; and limiting the instantaneous power when the result of the comparison is that the detected instantaneous power is equal to or greater than the power limit value.
Siemens Aktiengesellschaft

new patent

Aeroderivative jet engine accessory starter relocation to main shaft -- directly connected to hpc shaft

In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment.
General Electric Company

new patent

Controlling injection of bio-diesel into a gas turbine combustor

Certain embodiments may include systems and methods that comprise for injecting biofuel into a gas turbine system. The systems and methods comprise of storing a biofuel in a storage tank, injecting a first blend of biofuel into a first gas turbine, and injecting a second blend of biofuel in a second gas turbine concurrently with the injecting of the first blend into the first gas turbine.
General Electric Company

new patent

Gas turbine with a valve cooling system

The present application provides a gas turbine engine. The gas turbine engine may include a compressor air extraction system with a number of valves, an exhaust frame cooling system with an exhaust frame blower, and a turbine valve cooling system with one or more valve protection boxes surrounding one or more of the valves.
General Electric Company

new patent

Gas turbine facility

The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23..
8 Rivers Capital, Llc

new patent

Systems and methods for wheel space temperature management

The present application provides a gas turbine engine intended to be used in part in hot ambient conditions. The gas turbine engine may include a compressor, a turbine with a wheel space adjacent to a number of rotor wheels, and a wheel space water cooling system in communication with the wheel space to provide a flow of water thereto..
General Electric Company

new patent

Horizontal engine build stand

A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module..
United Technologies Corporation

new patent

Spoke locking architecture

A spoke locking arrangement comprising a washer seated in a seat defined in a structural ring of a gas turbine engine, the washer having a portion thereof plastically deformed into an anti-rotation notch defined in the structural ring, thereby locking the washer against rotation in the seat, the washer further comprising a set of holes for receiving corresponding bolts, and wherein the washer further has at least one anti-rotation tab at each hole, the anti-rotation tabs being deformable in engagement with the bolts to individually lock the same against rotation.. .
Pratt & Whitney Canada Corp.

new patent

Spoke mounting arrangement

A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring..
Pratt & Whitney Canada Corp.

new patent

Wheel space purge flow mixing chamber

Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm.
General Electric Company

new patent

Shroud assembly for a gas turbine engine

A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber.
General Electric Company

new patent

Wheel space purge flow mixing chamber

Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm.
General Electric Company

new patent

Systems and methods to facilitate enhancing turbine output using an auxiliary generator

A gas turbine engine system includes a gas turbine engine with a rotating element, at least one primary rotor shaft coupled to the rotating element, and a primary generator coupled to the at least one primary rotor shaft. The system further includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft.
General Electric Company

new patent

Module for a gas turbine

The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure..
Mtu Aero Engines Ag

new patent

Shroud assembly for a gas turbine engine

An assembly for mounting a circumferential shroud to a casing, including a plurality of arcuate shroud segments collectively forming the circumferential shroud. Each segment includes a circumferentially extending wall and a channel extending from the wall.
Rolls-royce Plc

new patent

Turbine cavity sealing assembly

Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting halo seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane..
United Technologies Corporation

new patent

Turbine slotted arcuate leaf seal

A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully.
General Electric Company

new patent

Additively manufactured connection for a turbine nozzle

Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band.
General Electric Company

new patent

Nozzle for a gas turbine engine

A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber.
General Electric Company

new patent

Gas turbine engine with a transition duct and corresponding manufacturing a transition duct

A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile.
Siemens Aktiengesellschaft

new patent

Additively manufactured bladed disk

A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone.
General Electric Company

new patent

Blade platform gusset with internal cooling

A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform.
United Technologies Corporation

new patent

Turbine blade

An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element.
General Electric Company

new patent

Turbine blade

An airfoil for a gas turbine engine can receive a flow of cooling fluid through a cooling circuit. The cooling circuit is defined within the airfoil comprising a supply passage and a leading edge cooling passage, the two passages being in fluid communication through a plurality of impingement orifices disposed within a cross-over rib disposed between and at least partially defining the passages.
General Electric Company

new patent

Gas turbine cooling apparatus

Disclosed herein is a cooling apparatus of a gas turbine including a compressor disk unit mounted in a gas turbine and provided with compressor cooling passages; the torque tube units provided in an adhering state to each other while being adjacent to the compressor disk unit and provided with a cooling air supply passage communicating with the compressor disk cooling passage; and a turbine disk unit provided with a turbine disk cooling passage communicating with the cooling air supply passage of the torque tube unit, in which the torque tube units are disposed between the compressor disk unit and the turbine disk unit and coupled therewith in an adhering state to each other along an axial direction of a rotation shaft mounted in the gas turbine and the cooling air supply passage is open in horizontal direction along the axial direction from an edge of the torque tube unit.. .
Doosan Heavy Industries Construction Co., Ltd.



Gas Turbine topics:
  • Gas Turbine
  • Gas Turbine Engine
  • Internal Combustion Engine
  • Distributed
  • Combustion
  • Uv Radiation
  • Exhaust Gas
  • Circulation
  • Downstream


  • Follow us on Twitter
    twitter icon@FreshPatents

    ###

    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.


    0.2734

    file did exist - 3141

    2 - 1 - 63