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Gas Turbine patents

      

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




 Dual-shaft gas turbine power generation system, and control device and control  gas turbine system patent thumbnailDual-shaft gas turbine power generation system, and control device and control gas turbine system
The dual-shaft gas turbine power generation system includes: a high-pressure gas turbine; a first rotating shaft connecting a compressor and the high-pressure gas turbine; an electric motor connected to the first rotating shaft; a governor which adjusts the amount of air taken into the compressor; a low-pressure gas turbine; a second rotating shaft connected to the low-pressure gas turbine; a synchronous power generator connected to the second rotating shaft; a frequency converter which converts the frequency of power transmitted between the synchronous power generator and the electric motor; and a control device which controls a frequency converter control device for controlling the frequency converter, and the governor, on the basis of a power output command value indicating the power to be outputted to an external grid.. .
Hitachi, Ltd.


 Maintenance event planning using adaptive predictive methodologies patent thumbnailMaintenance event planning using adaptive predictive methodologies
A generalized autoregressive integrated moving average (arima) model for use in predictive analytics of time series is based upon creating all possible arima models (by knowing a priori the largest possible values of the p, d and q parameters forming the model), and utilizing the results of at least two different performance measures to ultimately choose the arima(p,d,q) model that is most appropriate for the time series under study. The method of the present invention allows each parameter to range over all possible values, and then evaluates the complete universe of all possible arima models based on these combinations of p, d and q to find the specific p, d and q parameters that yield the “best” (i.e., lowest value) performance measure results.
Siemens Aktiengesellschaft


 Combustion device for gas turbine engine patent thumbnailCombustion device for gas turbine engine
A combustor includes: a combustion liner having a combustion chamber formed therein; a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion; and a supplemental burner. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately.
Kawasaki Jukogyo Kabushiki Kaisha


 Gas turbine combustor patent thumbnailGas turbine combustor
A gas turbine combustor includes: an inner casing; an outer casing; an annular flow path disposed between the inner casing and the outer casing; a fuel header; a plurality of fuel nozzles supported concentrically on the fuel header; an air hole plate having a plurality of air holes associated with the respective fuel nozzles; a guide having a wall portion and a bent portion; and an outer peripheral flow path defined between the outer peripheral surface of the air hole plate and the inner casing.. .
Mitsubishi Hitachi Power Systems, Ltd.


 Combustor for gas turbine engine patent thumbnailCombustor for gas turbine engine
A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner.
Pratt & Whitney Canada Corp.


 Valve for a fuel injector patent thumbnailValve for a fuel injector
A fuel injector for injecting fuel in a burner of a gas turbine where the fuel injector has a body with an inner hole and a valve element which is slideably arranged inside the inner hole. The body has a fuel inlet which is formed into the body for injecting fuel into the inner hole, wherein the fuel inlet is coupleable to a fuel supply line.
Siemens Aktiengesellschaft


 Apparatus and  dampening acoustics patent thumbnailApparatus and dampening acoustics
An apparatus for dampening acoustic pressure oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor. The apparatus includes at least one resonating tube with a closed end, an open end, and a cavity therebetween.
General Electric Company


 Compressor variable vane assembly patent thumbnailCompressor variable vane assembly
A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof.
Pratt & Whitney Canada Corp.


 Gas turbine engine with axial movable fan variable area nozzle patent thumbnailGas turbine engine with axial movable fan variable area nozzle
A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area..
United Technologies Corporation


 Gas turbine engine blade platform modification patent thumbnailGas turbine engine blade platform modification
A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation.
General Electric Company


Counter-rotating compressor

A compressor is described which includes a non-axial first rotor, and a second rotor disposed immediately downstream from the first rotor and being co-axial therewith about a longitudinal axis of rotation. The second rotor rotates in a direction opposite the non-axial first rotor to discharge fluid flow into an uninterrupted passage between an outlet of the second rotor and one of a downstream combustor or a further compression stage.

Gas turbine compressor stage

σ>−1.33×arax+5.16.. .

Gas turbine engine with axial movable fan variable area nozzle

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area..
United Technologies Corporation

Gas turbine engine with axial movable fan variable area nozzle

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area..
United Technologies Corporation

Gas turbine engine with axial movable fan variable area nozzle

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area..
United Technologies Corporation

Gas turbine combustion control device and combustion control method and program therefor

A combustion control device (50) is installed in a gas turbine including a compressor (2), combustors (3), a turbine (4), a bleed air pipe (12) through which bleed air is returned to an inlet of an air intake facility (7), and an air bleed valve (22) that regulates the amount of bleed air extracted. The combustion control device (50) includes: a fuel distribution setting unit (70) that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section (81) that sets the valve openings of fuel regulating valves.
Mitsubishi Hitachi Power Systems, Ltd.

Method for starting a gas turbine

A method of starting a gas turbine is provided, comprising the step of providing an apparatus for regulating the flow of fuel in a gas turbine, the apparatus comprising a main line connecting a fuel source to a nozzle array; and an auxiliary line connecting the fuel source to the nozzle array. The method further comprises the steps of keeping the main line sealed while increasing the auxiliary line fuel flow rate; firing the gas turbine while keeping the main line sealed; and after the combustion has started in the gas turbine, opening the main line for increasing the main line fuel flow rate; wherein the auxiliary line maximum flow rate is less than the main line maximum flow rate..
Nuovo Pignone Srl

Control system and controlling a variable area gas turbine engine

A method of controlling a variable area gas turbine engine includes, running the variable area turbine engine at initial settings, monitoring two sets of operating parameters of the engine at the initial settings, and deducing vane angles of adjustable vanes without directly measuring the vane angles from mapped data of the two sets of operating parameters of a similar engine operated while direct vane angle measurements were being recorded.. .
United Technologies Corporation

Ejector based external bleed system for a gas turbine engine

A method and system for providing a cooling flow from a compressor to a turbine in a gas turbine engine. First, second and third cooling air flows are provided from the compressor through respective ejectors as external bleed air flows to stages of the turbine.
Siemens Energy, Inc.

Gas turbine plant and improving existing gas turbine plant

A gas turbine plant comprises: a gas turbine having a compressor configured to compress air, a combustor configured to mix compressed air compressed by the compressor with fuel to generate combustion gas, a turbine connected to the compressor and configured to acquire rotary power by the combustion gas, and an air bleeding piping configured to supply the compressed air bled off from the compressor to the turbine as cooling air; and an auxiliary compressed air supply apparatus having a separately placed compressor different from the compressor, a motor configured to rotate the separately placed compressor, and an auxiliary compressed air piping configured to connect the separately placed compressor to the air bleeding piping to supply auxiliary compressed air compressed by the separately placed compressor to the air bleeding piping. The gas turbine further includes a cooling apparatus connected to the air bleeding piping and configured to cool down the cooling air..
Mitsubishi Hitachi Power Systems, Ltd.

Gas turbine engine comprising a starter engaged with a low-pressure body

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body , a high-pressure rotating body, and a starter to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body , for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.. .
Safran Aircraft Engines

Waste heat recovery device, gas turbine plant provided with same, and waste heat recovery method

A waste heat recovery device includes: a low-boiling-point medium rankine cycle in which a low-boiling-point medium circulates while the low-boiling-point medium is repeatedly condensed and evaporated; a heated water line that guides liquid water, which is heated here, to the low-boiling-point medium rankine cycle from a waste heat recovery boiler; and a water recovery line that returns the water, which has passed through the low-boiling-point medium rankine cycle, to the waste heat recovery boiler. The low-boiling-point medium rankine cycle includes a heater that heats the low-boiling-point medium by exchanging heat between the low-boiling-point medium, which is a liquid, and liquid water, which has passed through the heated water line..
Mitsubishi Hitachi Power Systems, Ltd.

Method of creating heat transfer features in high temperature alloys

A method for forming a gas turbine engine component comprises the steps of forming a first portion from a high temperature alloy material, and forming a second portion from the high temperature alloy material, the first and second portions each defining an external surface and an internal surface. At least one heat transfer feature is formed directly on the internal surface of at least one of the first and second portions.
United Technologies Corporation

Active clearance control for gas turbine engine

A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit.
United Technologies Corporation

Advanced stationary sealing cooled cross-section for axial retention of ceramic matrix composite shrouds

In one aspect, the present subject matter is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall.
General Electric Company

Mixing chambers for turbine wheel space cooling

The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle..
General Electric Company

Gas turbine engine rotor balancing

A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs.
Pratt & Whitney Canada Corp.

System and method to determine total air temperature from turbofan bypass flow temperature

A system and method for calculating aircraft total air temperature from bypass flow temperature in a turbofan gas turbine engine having a bypass flow duct includes sensing aircraft speed (m), sensing engine fan speed (n1), sensing core engine speed (n2), and sensing bypass air flow temperature (t15) in the bypass flow duct. Total air temperature (tat) is calculated as a function of the sensed aircraft speed, the sensed engine fan speed, the sensed core engine speed, and the sensed bypass air flow temperature.
Honeywell International Inc.

Assembly group with a combustion chamber shingle for a gas turbine

An assembly group for a combustion chamber of a gas turbine includes a combustion chamber shingle with a mounting element and a bolt formed as a separate structural component for supporting the combustion chamber shingle at a wall of the combustion chamber. The mounting element has a reception area into which a bolt head of the bolt is inserted transversely with respect to a longitudinal axis of the bolt and anchored therein in a form-fit manner.
Rolls-royce Deutschland Ltd & Co Kg

System and method having annular flow path architecture

A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a rotational axis of a gas turbine engine, and an axis of the combustion chamber is acutely angled relative to the rotational axis.
General Electric Company

Turbomachine blade

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (a) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (b) transversely to the first matrix axis (a) and in which at least one impulse element (31) is disposed with play, the first matrix axis (a) and an axis of rotation (r) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.. .
Mtu Aero Engines Ag

Hydrodynamic seals in bearing compartments of gas turbine engines

In one aspect, the present disclosure is directed to a bearing compartment sealing system including a bearing for supporting a shaft. A housing encloses the bearing and defines a compartment for holding lubricant therein.
General Electric Company

Exhaust chamber inlet-side member, exhaust chamber, gas turbine, and last-stage turbine blade removal method

An object of the present invention is to easily remove last-stage turbine blades. Provided is an exhaust chamber inlet-side member that has an annular shape around a rotor so as to form a part of an inner diffuser at a position facing, from the axially downstream side, base ends of last-stage turbine blades disposed on the most downstream side in the axial direction, and that is divided in the circumferential direction and provided so as to be detachable from the inner diffuser.
Mitsubishi Hitachi Power Systems, Ltd.

Device for bounding a flow channel of a turbomachine

A device for bounding a flow channel of a turbomachine, comprising a wall that, viewed in the circumferential direction of the turbomachine, has a multiplicity of wall segments, and including a multiplicity of outer segments that extend radially around the outside of the wall segments; each wall segment having a uniformly curved first cross-sectional contour; each outer segment including at least one second cross sectional contour that deviates from the uniformly curved first cross-sectional contour; the second cross-sectional contour having a multiplicity of depressions that are inwardly directed in the radial direction of the gas turbine; at least a portion thereof being attached to the radially outer surface of a corresponding wall segment.. .
Mtu Aero Engines Ag

Gas turbine rotor cover

A gas turbine rotor cover includes a body, the body having an inner side facing towards a central axis and an outer side facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction and a circumferential direction relative to the central axis. An inner layer of insulation is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction.
Ansaldo Energia Switzerland Ag

Flow control device for rotating flow supply system

This disclosure describes a removable flow control device which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade and rotor assembly and may include a flow modifier for directing flow through a junction at which cooling channels intersect and are in fluid communication.

Seal assembly for turbine engine component

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier and configured to abut against at least two sealing surfaces. A method of sealing between adjacent components of a gas turbine engine is also disclosed..
United Technologies Corporation

Ceramic matrix composite materials with rare earth phosphate fibers and methods for preparing the same

Disclosed is a ceramic matrix composite (cmc) material including rare earth phosphate ceramic fibers embedded in a ceramic matrix, wherein the ceramic matrix also optionally includes a rare earth phosphate material. Methods for manufacturing the cmc material and gas turbine engine components formed of the cmc material are also disclosed..
Honeywell International Inc.



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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