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Document Title |
WO/2016/056180A1 |
A fuel injecting device (36) for a combustor (12) has a pilot burner (40) and a main burner (4). The main burner (4) has at least one first fuel injection port (41a) to supply a first fuel to an upstream section of a combustion chamber (...
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WO/2016/055738A1 |
Method for notifying an authorization to completely shut down an aircraft gas turbine engine and aircraft gas turbine engine comprising a device for such notification, the method comprising, following the detection (E10) that the engine ...
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WO/2016/055354A1 |
The invention relates to a gas turbine (1) comprising at least one rotor (2) and an inner housing part (3) in order to form an annular chamber (4) between the rotor (2) and the inner housing part (3). The annular chamber (4) is fluidical...
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WO/2016/055278A1 |
A (micro) gas turbine arrangement has a gas turbine device (12) with a combustion chamber system (28), a turbine (30) driven by an exhaust gas stream (32) from the combustion chamber system, and a compressor (22) for supplying the combus...
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WO/2016/052205A1 |
In the present invention, gas turbine equipment is provided with a gas turbine (10) for which a mixed gas of natural gas and boil-off gas is the fuel, a fuel flow control valve (31) for regulating the flow rate of the fuel supplied to th...
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WO/2016/042960A1 |
A combustion burner comprises: a nozzle; a swirl vane that has a fuel injection hole for injecting fuel, is provided around the nozzle in an annular air flow channel extending along the axial direction of the nozzle, and is configured so...
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WO/2016/038672A1 |
In order to enhance the tracking performance of power generation equipment with respect to a load variation and increase the reliability of the power generation equipment, a dynamic characteristic model simulating the dynamic characteris...
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WO/2016/039943A1 |
Systems and methods for regulating a bulk flame temperature in a dry low emission engine are provided. According to one embodiments of disclosure, a method may include measuring an exhaust gas temperature (EGT) and determining a target E...
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WO/2016/035433A1 |
Failure detection accuracy is improved by providing: an accumulated data storage unit (30); a unit space generating means (13) which extracts, from the accumulated data storage unit, sensor values for a unit space to be used by an MT sys...
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WO/2016/035416A1 |
A gas turbine control device comprising a compressor, a combustor, and a turbine, executes load control that varies an operation control point for controlling gas turbine operation in accordance with the gas turbine load. The gas turbine...
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WO/2016/031355A1 |
A control device (14) for a gas turbine in which indrawn air is compressed by a compressor to produce compressed air, the compressed air is mixed with fuel supplied from a combustor and is burned to generate combustion gas, and the turbi...
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WO/2016/030616A1 |
The invention relates to a device for starting a gas turbine, comprising a starter system able on command to drive said gas turbine in rotation. The starter system comprises means for receiving information representative of the rotationa...
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WO/2016/030352A1 |
The invention relates to a method for operating a gas turbine (1) in the event of load shedding, which comprises the following steps: generating an electrical signal (10) by means of the control system (11) in order to initiate load shed...
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WO/2016/023987A1 |
The invention relates to a method for operating a power plant (1) comprising a gas turbine (2) and an emergency fuel system (11). In a normal operating state, gas (5) is supplied from a supply line (3) to the combustion process (4) of th...
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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...
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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 flowin...
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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...
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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...
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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...
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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 ...
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WO/2016/012713A1 |
The invention relates to an overspeed protection device of an aircraft engine
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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...
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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...
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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...
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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...
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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...
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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 supplying...
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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...
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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 speed ...
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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 (2...
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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...
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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 ...
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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 ...
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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...
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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) ...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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