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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


Fan blade root integrated sealing solution

United Technologies

Fan blade root integrated sealing solution

Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions

Siemens Aktiengesellschaft

Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions

Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions

Continental Automotive

Turbine rotor for an exhaust-gas turbine and method for producing the turbine rotor

Date/App# patent app List of recent Gas Turbine-related patents
04/16/15
20150105966
 Condition based lifing of gas turbine engine components patent thumbnailnew patent Condition based lifing of gas turbine engine components
A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component..
Solar Turbines Incorporated
04/16/15
20150104318
 Turbine rotor for an exhaust-gas turbine and  producing the turbine rotor patent thumbnailnew patent Turbine rotor for an exhaust-gas turbine and producing the turbine rotor
A turbine rotor as a turbine impeller made of a high-temperature-resistant metal alloy and a rotor shaft made of steel. The impeller hub and the rotor shaft end are connected together in a metallurgically bonded manner by way of a brazed connection.
Continental Automotive Gmbh
04/16/15
20150104315
 Fan blade root integrated sealing solution patent thumbnailnew patent Fan blade root integrated sealing solution
A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades.
United Technologies Corporation
04/16/15
20150104306
 Fan casing arrangement for a gas turbine engine and related method patent thumbnailnew patent Fan casing arrangement for a gas turbine engine and related method
A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns.
Rolls-royce Plc
04/16/15
20150104298
 Tip treatment bars in a gas turbine engine patent thumbnailnew patent Tip treatment bars in a gas turbine engine
There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support.
Rolls-royce Plc
04/16/15
20150101345
 Seal assembly for a gap between outlet portions of adjacent transition ducts in a gas turbine engine patent thumbnailnew patent Seal assembly for a gap between outlet portions of adjacent transition ducts in a gas turbine engine
A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position.
04/16/15
20150101344
 Systems and methods for bypassing a coalescer in a gas turbine inlet patent thumbnailnew patent Systems and methods for bypassing a coalescer in a gas turbine inlet
A system including an air intake subsystem having a housing is provided. A coalescer having a frame is disposed inside the housing.
Bha Altair, Llc
04/16/15
20150101343
 Gas turbine combustor patent thumbnailnew patent Gas turbine combustor
A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device.
Mitsubishi Heavy Industries, Ltd.
04/16/15
20150101341
 Method for a part load co reduction operation for a sequential gas turbine patent thumbnailnew patent Method for a part load co reduction operation for a sequential gas turbine
The invention concerns a method for a part load co reduction operation and a low-co emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor.
Alstom Technology Ltd
04/16/15
20150101340
 System and  improving efficiency of a gas turbine engine patent thumbnailnew patent System and improving efficiency of a gas turbine engine
A gas turbine engine is presented. The gas turbine engine includes a control unit having a first bypass channel that is coupled between an outlet of a first turbine and an inlet of a second turbine.
General Electric Company
04/16/15
20150101339
new patent

Energy efficient pump system


A fuel system for a gas turbine engine, which includes a combustor section and an actuator, includes a fuel source, a combustor system, and an actuation system. The combustor system includes a combustor pump that is fluidly connected to the fuel source and to the combustor section, with the combustor pump being mechanically connected to and powered by an electric motor.
Hamilton Sundstrand Corporation
04/16/15
20150101336
new patent

Cooling structure for gas turbine combustor liner


In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).. .
04/16/15
20150101335
new patent

Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions


A gas turbine combustion chamber with an inner housing and an outer housing the inner housing having an inner wall element with a first hole arrangement and a second hole arrangement is provided. The inner wall element envelopes a burner volume.
Siemens Aktiengesellschaft
04/16/15
20150101332
new patent

Combustion chamber of a gas turbine with improved acoustic damping


A combustion chamber of a gas turbine includes an optimized arrangement of acoustic dampers.. .
Alstom Technology Ltd
04/16/15
20150101331
new patent

Gas turbine engine


A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall.
Rolls-royce Plc
04/09/15
20150098832

Method and system for relieving turbine rotor blade dovetail stress


A system for relieving stress on a turbine rotor blade dovetail in a gas turbine is provided. At least one turbine rotor blade includes a dovetail that is axially insertable into a correspondingly-shaped slot defined in a turbine disk.
General Electric Company
04/09/15
20150098831

Rotor blade arrangement and gas turbine


A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19)..
Alstom Technology Ltd
04/09/15
20150098830

Assembly fixture for a stator vane assembly


A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing.
United Technologies Corporation
04/09/15
20150098829

Shroud assembly and seal for a gas turbine engine


A shroud assembly having rope seals disposed between the shroud hangers and the surrounding case structure.. .
General Electric Company
04/09/15
20150098826

Apparatus and assembling a damper bearing assembly


A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing.
General Electric Company
04/09/15
20150098816

System and controlling backbone bending in a gas turbine engine


A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange.
General Electric Company
04/09/15
20150098811

Adjustable bracing apparatus and assembly gas turbine exhaust diffuser


Length adjustable braces (56, 56a-d) attached between a gas turbine exhaust diffuser (40) and an exhaust casing (34) along a horizontal joint (50) between upper and lower halves (40a, 40b) of the outer diffuser shell. Brace lengths are adjusted to align bolt holes (52a, 52b) in respective bolt bosses (43a, 43b) on the upper and lower halves of the shell.
04/09/15
20150098808

Method and system to facilitate sealing in gas turbines


A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member.
General Electric Company
04/09/15
20150098798

Brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another


A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components.
Mtu Aero Engines Ag
04/09/15
20150098791

Method and system for passive clearance control in a gas turbine engine


A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.. .
General Electric Company
04/09/15
20150097582

Sensor for measuring blade tip clearance in gas turbines


Determining a distance between stationary and moving portions of a turbo machine including generating, by a fixed gap capacitive probe, a first output signal based on a characteristic of a gas in a gas flow path of the turbo machine, wherein the fixed gap capacitive probe is located in the stationary portion and is configured to sense a characteristic of a gas flowing through the gas flow path. Also, a variable gap capacitive probe, located adjacent the fixed gap capacitive probe, is used to generate a second output signal based on a distance between the variable gap capacitive probe and the moving portion, wherein the variable gap probe is configured to capacitively couple to the moving portion of the turbo machine.
04/09/15
20150097376

Method of operating an internal combustion engine coupled to a generator


A method of operating an internal combustion engine coupled to a generator in the event of a grid fault of a power supply grid connected to the generator, in particular in the event of a dynamic grid voltage drop, wherein the internal combustion engine includes a turbocharger having a compressor in an air feed duct of the internal combustion engine and an exhaust gas turbine coupled to the compressor in an exhaust gas duct of the internal combustion engine, wherein there is provided at least one bypass valve for bypass of the compressor and/or for bypass of the exhaust gas turbine, wherein upon or after detection of the grid fault the at least one bypass valve is at least temporarily actuated.. .
Ge Jenbacher Gmbh & Co Og
04/09/15
20150096963

Laser cladding with programmed beam size adjustment


A method for heating an irregularly shaped target surface (28, 36) with an energy beam (12, 48) with a controlled power density as the beam progresses across the surface in order to control a cladding process. In one embodiment, widths (y) of respective rectangular diode laser beam images (22, 24, 26) are controlled in response to a local width of a gas turbine blade tip (20), and a power level of the diode laser is linearly controlled in response to the width of the respective image in order to maintain an essentially constant power density across the blade tip.
04/09/15
20150096306

Gas turbine airfoil with cooling enhancement


A turbine nozzle vane segment includes one or more nozzle vanes extending between radially inner and outer side walls, each nozzle vane having a peripheral edge wall extending between a leading edge and a trailing edge of the vane. In one exemplary embodiment, at least one substantially radially-oriented cooling channel is formed in the peripheral edge wall at the leading edge, with openings at opposite ends of the cooling channel.
General Electric Company
04/09/15
20150096304

Air accelerator on tie rod within turbine disk bore


A gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod therethrough. First and second bore annular flowpaths are radially located between first and second stage disk bores and tie rod.
General Electric Company
04/09/15
20150096303

Gas turbine engine with high speed low pressure turbine section


A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.. .
United Technologies Corporation
04/09/15
20150096302

Combustor heat-shield cooling via integrated channel


A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell.
Pratt & Whitney Canada Corp.
04/02/15
20150093252

Internally cooled airfoil


An internally cooled airfoil for a gas turbine engine has a hollow airfoil body defining a core cavity. An insert is mounted in the core cavity.
Pratt & Whitney Canada Corp.
04/02/15
20150093251

Cooling module design and cooling components of a gas turbine system


A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls.
Mikro Systems, Inc.
04/02/15
20150093249

Blade for a gas turbine


Disclosed is a blade for a gas turbine, in particular for an aircraft engine, wherein the blade comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. Also disclosed are a blade cluster having at least one such blade for a gas turbine, a method for producing such a blade cluster and a gas turbine..
Mtu Aero Engines Ag
04/02/15
20150093248

Retainer plate


A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot.
Rolls-royce Plc
04/02/15
20150093211

Bolt for gas turbine engine rotor


The bolt has, in sequence along a bolt axis: a threaded portion, a thread run-out portion, a shank, and a head, the threaded portion having a thread with a given root radius and a given depth, the thread run-out portion connected to the shank via a thread run-out fillet having a thread run-out fillet radius, the thread run-out fillet radius being between two and six times the thread root radius.. .
Pratt & Whitney Canada Corp.
04/02/15
20150089959

Gas turbine engine shaft bearing configuration


A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path.
United Technologies Corporation
04/02/15
20150089958

Gas turbine engine with high speed low pressure turbine section


A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.. .
United Technologies Corporation
04/02/15
20150089956

Method of exhaust gas treatment for a gas turbine system and exhaust gas treatment assembly


The invention relates to a method for operating a gas turbine system, wherein the gas turbine system includes a compressor, a combustor, a heat recovery steam generator, a scrubber, a direct contact cooler. The method includes introducing the scrubbing fluid discharged from the scrubber into the direct contact cooler, contacting the scrubbing fluid in the direct contact cooler with the exhaust gas discharged from the heat recovery steam generator in order to remove a portion of nitrogen oxide therefrom; feeding the exhaust gas discharged from the direct contact cooler into the compressor.
Alstom Technology Ltd
04/02/15
20150089955

Gas turbine with cooling air cooling operation of a gas turbine at low part load


A gas turbine and method for operating a gas turbine, includes a compressor, a combustor, a turbine and a cooling air cooling system having at least a first cooling air line going from a first bleed of the compressor to the turbine, and at least one second cooling air line at a downstream position of the compressor relative to the first cooling air line. A heat exchanger is arranged in the second cooling air line for cooling the extracted air of higher pressure.
Alstom Technology Ltd.
04/02/15
20150089953

Systems and methods for preventing fuel leakage in a gas turbine engine


Systems and methods for preventing fuel leakage in a gas turbine engine are provided. A fuel accumulation system includes a control valve section fluidly coupled to a fuel manifold passage and an accumulator valve section fluidly coupled at a first side to the control valve section.
General Electric Company
04/02/15
20150089952

Inclined fuel injection of fuel into a swirler slot


A combustor for a gas turbine is provided. The combustor includes a pre-combustion chamber having a centre axis and a swirler which is mounted to the pre-combustion chamber.
Siemens Aktiengesellschaft
04/02/15
20150089920

Airblast fuel injector


An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough.
Rolls-royce Plc
04/02/15
20150089918

Gas turbine lubrication systems


A casing for a fan drive gear system includes a cast body with an upper and a lower portion. The cast body defines an oil inlet and an oil outlet arranged below the oil outlet.
United Technologies Corporation
03/26/15
20150086381

Internally cooled airfoil


An internally cooled airfoil for a gas turbine engine has a hollow airfoil body including pressure and suction sidewalls defining a cooling passage therebetween. A combination of pedestal and trip-strips are used in the cooling passage to enhance heat transfer while minimizing the coolant pressure drop across these features..
Pratt & Whitney Canada Corp.
03/26/15
20150086361

Axial rotor portion and turbine rotor blade for a gas turbine


A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap.
Siemens Aktiengesellschaft
03/26/15
20150086352

Gas turbine engine inlet assembly and making same


A method of fabricating an inlet assembly for a gas turbine engine, the method including defining an intake duct of the inlet assembly between first and second space apart inlet case portions, locating at least one strut across the intake duct, each strut having a proximal end made integral to the first inlet case portion and an opposed distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, while maintaining the distal end of each strut in the respective strut-receiving aperture, adjusting the relative position of the first inlet case portion and the second inlet case portion until a predetermined throat dimension of the intake duct is obtained, and locking the adjusted relative position by attaching the second inlet case portion to each strut. An inlet assembly and gas turbine engine with inlet assembly as also disclosed..
Pratt & Whitney Canada Corp.
03/26/15
20150086339

Diffuser with strut-induced vortex mixing


A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield.
03/26/15
20150086334

Centrifugal compressor provided with a marker for measuring wear and a monitoring wear using said marker


A device and method for precise measurement of erosion of compressors, without removing an engine, and with easy positioning. A centrifugal compressor of a gas turbine with a radial air inlet includes an impeller including blades and a casing for an air stream to flow in the blades of the impeller.
Turbomeca
03/26/15
20150086330

Gas turbine casing load sharing mechanism


A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall.
General Electric Company


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

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This listing is a sample listing of 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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