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Matches 251 - 300 out of 8,850

Document Document Title
WO/2016/020607A1
The quick-assist device applies to a free-turbine turbomachine (11) of an aircraft comprising at least a first free-turbine turbomachine (11) provided with a gas generator, combined with an electric machine (12) that can operate as a sta...  
WO/2016/021298A1
 This flow ratio calculation device is provided with: a flow ratio calculator (141p) for using a predetermined relationship between a first parameter that can represent the combustion state in a combustor and the flow ratio of fuel flo...  
WO/2016/021390A1
A gas turbine equipped with: a plurality of fuel lines; a combustor that generates combustion gas by burning the fuel from the plurality of fuel lines in compressed air; and a turbine driven by the combustion gas. A flow volume ratio cal...  
WO/2016/016982A1
With regard to a load running system that comprises a plurality of compressors that compress a fuel gas and supply the compressed fuel gas to a load apparatus, this compressor control device comprises: a feedforward control signal genera...  
WO/2016/016983A1
A control device (101) that controls a fuel gas supply system (100) that has: a compressor (1) that supplies compressed fuel gas to a load apparatus (15); an inflow amount regulating means (5) that regulates the amount of fuel gas that f...  
WO/2016/016988A1
A control device (101) that controls a fuel gas supply system (100) that comprises: a compressor (1) that supplies compressed fuel gas to a load apparatus (15); an inflow amount regulating means (5) that regulates the amount of fuel gas ...  
WO/2016/012713A1
The invention relates to an overspeed protection device of an aircraft engine  
WO/2016/012715A1
The main subject matter of the invention is a system (1) for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisa...  
WO/2016/009155A1
There is proposed a method for controlling a bistable shutoff vale for an aircraft engine, involving the steps of: emitting a closure signal on one of the control channels - emitting an open signal on the other control channel, the metho...  
WO/2016/003517A2
A thrust reverser system may comprise a cascade radially positioned about a centerline of an engine or a nacelle centerline. Various cascade features may be positioned at a constant radius from the centerline while other features vary ac...  
WO/2016/003932A1
In a gas turbine system (52) having an exhaust gas recirculation system (54) receiving exhaust from the gas turbine system and recycling the exhaust gas back to the gas turbine system, a blower (580) with variable guide vanes (586) is po...  
WO/2015/193979A1
A multi-shaft variable-speed gas turbine device characterized by being provided with: a multi-shaft gas turbine including a gas turbine compressor, a gas turbine combustor, a gas generator provided with a first turbine that causes the ga...  
WO/2015/188313A1
A fuel supply system is provided having a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system. The first fuel gas compressor and the sec...  
WO/2015/186611A1
 A water supply step (S1) for supplying water to a liquid-fuel channel of a nozzle is executed during a liquid fuel supply state (Mo) in which only liquid fuel is supplied to the nozzle, a post-switch water-purging step (S3) for supply...  
WO/2015/181463A1
The method according to the invention for control of a thrust of a turbojet engine, having fuel flow regulated by means of an upper stop for protection against pumping of a compressor of the turbojet engine, comprises: — obtaining (E10...  
WO/2015/182327A1
 A control device (100) having a fuel equivalent value calculator (150) for establishing the flow rate of fuel supplied to a gas turbine in accordance with a target value difference (∆Nt) between an actual speed (Nr) and a target spe...  
WO/2015/181938A1
 A gas turbine composite power generation device having a gas turbine (2A), a power generator (3) for generating power through the drive force of a turbine (1), a first control device (20A) for controlling the output of the gas turbine...  
WO/2015/130356A3
A fuel system for a gas turbine engine includes a fuel conditioner. The fuel conditioner has an ice debris separator, a fuel pump, a heat exchanger, and an air oil cooler. The ice debris separator has a fuel inlet and a fuel outlet. The ...  
WO/2015/178897A1
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 t...  
WO/2015/177409A1
An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is ...  
WO/2015/178389A1
Provided are a combustor replacement method and a gas turbine plant with which a combustor can be efficiently replaced using existing facilities. The combustor replacement method has: a step (S14) in which a first combustor (212) having ...  
WO/2015/179044A1
A gas turbine engine includes a compressor, a combustor adjacent the compressor, a turbine adjacent the combustor, a shaft, a motor, a primary variable frequency drive, an auxiliary variable frequency drive, and an auxiliary motor. The m...  
WO/2015/178418A1
A cooling device (60) is provided with a high-temperature-component cooling system (70) for guiding air to a high-temperature component (41) of a gas turbine (10). The high-temperature-component cooling system (70) has a compressor (77) ...  
WO/2015/177442A1
The invention relates to a turbine engine fuel injection architecture including: two fuel injection manifolds (30A, 30B), each manifold being suitable for dispensing a fuel flow to at least one associated injector; a main fuel-proportion...  
WO/2015/169565A1
The invention relates to a method for operating a burner assembly, in particular a burner assembly of a gas turbine, wherein an evaluation variable representing the combustion stability is determined and at least one control variable is ...  
WO/2015/169586A1
The invention relates to a method for selecting operating points of a gas turbine while taking into consideration at least one controlled variable, the operating points being defined at least by parameter combinations of manipulated vari...  
WO/2015/171582A1
The subject matter of this specification can be embodied in, among other things, a method that includes providing a fluid at a fluid inlet fluidically connected to an input fluid path, providing a fluid outlet fluidically connected to an...  
WO/2015/130363A3
In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operatio...  
WO/2015/166597A1
Provided is a gas turbine combustor and the like capable of maintaining flame-holding performance through suppressing the amount of generated NOx while suppressing burning of the area around a pilot nozzle including the pilot nozzle itse...  
WO/2015/068176A3
A method and system for determining one or more precursors to control blowout in a combustor is provided. The method includes obtaining a time series signal corresponding to a dynamic state variable of the combustor. The method includes ...  
WO/2015/116283A3
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pres...  
WO/2015/155142A1
The invention relates to a gas turbine (100) assembly comprising a first shaft (101), a first compressor (102) and a first turbine (103) mounted on the first shaft, a combustor (104) between the first compressor (102) and the first turbi...  
WO/2015/157011A1
A combined ball valve for compressor bleed air modulation is provided. The combined ball valve includes a housing defining an inlet, and first and second outlets. A metering element is positioned within the housing and within a flow path...  
WO/2015/150088A1
The invention relates to a gas-turbine system (2) of a power plant, said system comprising: a compressor (4); an annular combustion chamber (10) having a burner (14); and a turbine (6) coupled to the compressor (4). The gas turbine syste...  
WO/2015/151621A1
This jet engine is provided with an inlet that takes in air, a combustor (12) that combusts a fuel using air, and a fuel control unit (37) that controls the supply of fuel. The combustor (12) is provided with a fuel supply unit (22) that...  
WO/2015/150056A1
The invention relates to a pressure regulating device (1) for a gas supply system (3) of a gas turbine plant (5), comprising a pressure reduction unit (7) for reducing the pressure of an inflowing gas, in particular a combustion gas, a c...  
WO/2015/146786A1
The present invention is provided with: a compressor (11) that compresses air (A); a combustor (21) that combusts a fuel (F) in the compressed air (A) and generates a combusted gas (G); a plurality of cooled air coolers (54) that extract...  
WO/2015/145037A1
The invention relates to an architecture of a multiple-engine helicopter propulsion system comprising turbine engines (1, 2) which are connected to a power transmission gearbox (3), comprising: a hybrid turbine engine (1) able to operate...  
WO/2015/145041A1
The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4...  
WO/2015/147143A1
In a method for operating a multi-shaft combined cycle plant, a low load mode for adjusting the output of the multi-shaft combined cycle plant by adjusting only the output of a gas turbine, and a high load mode in which the output of the...  
WO/2015/146376A1
This jet engine comprises an inlet and a combustor. The inlet takes in air. The combustor combusts a fuel by using said air. The combustor (12) includes an injector (20) that is provided with a plurality of openings (31a, 31b) for inject...  
WO/2015/145036A1
The invention relates to the architecture of a multi-engine helicopter propulsion system comprising turboshaft engines, each turboshaft engine comprising a gas generator (17, 27) and a free turbine (10, 20) rotated by the gases from the ...  
WO/2015/145042A1
The invention relates to an architecture of a multi-engine helicopter propulsion system comprising turbine engines (1, 2) connected to a power transmission gearbox (3), and a low-voltage on-board DC network (7) intended to power helicopt...  
WO/2015/146994A1
A combustion control device (50) that is equipped to a gas turbine that comprises a compressor (2), a combustor (3), a turbine (4), extraction piping (12) that returns extracted air to the inlet of an intake apparatus (7), and an extract...  
WO/2015/145077A1
Assistance device (100) for a free turbine turbomachine (TAG1) of an aircraft comprising at least two free turbine turbomachines (TAG1, TAG2), the device comprising an electric starter machine (D1) for providing prolonged assistance to t...  
WO/2015/145076A1
Assistance device (100) for an aircraft free turbine turbomachine (TAG1), the device comprising means (K11, CVS1) for electrically powering a coil (SU) of a rotary starter machine (GD1), referred to as first coil, in order to provide a f...  
WO/2015/142612A1
A method of monitoring for combustion anomalies in a gas turbomachine includes sensing an exhaust gas temperature at each of a plurality of temperature sensors arranged in an exhaust system of the gas turbomachine, comparing the exhaust ...  
WO/2015/139949A1
The invention introduces a method for operating a gas turbine plant (1) having a gas turbine (100) and an electric generator (200) driven by the gas turbine (100). The method has at least the following steps: detecting an instantaneous p...  
WO/2015/140200A1
Method of starting a gas turbine, comprising the steps of providing an apparatus (1) for regulating the flow of fuel in a gas turbine, the apparatus (1) comprising a main line (4) connecting a fuel source (2) to a nozzle array (N); an au...  
WO/2015/141561A1
A combustor (10) is provided with: a nozzle (25) having formed therein an air jet section (51) that causes air to be jetted from a nozzle section (25s); a cylindrical member (26) that covers the nozzle (25) from the outer peripheral side...  

Matches 251 - 300 out of 8,850