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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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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 ...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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WO/2015/142318A1 |
A system for monitoring air flow into a compressor section of a turbine engine includes a chamber upstream from an inlet of the compressor section and a plurality of filter packages. The filter packages are in fluid communication with at...
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WO/2015/130356A2 |
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 ...
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WO/2015/129498A1 |
A fuel control device is provided with: a combustion temperature estimated value calculator for using atmospheric conditions, an opening degree command value of a valve for controlling the amount of air mixed and combusted with fuel, and...
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WO/2015/128193A1 |
The invention relates to a method for operating a stationary gas turbine (1) at partial load, comprising at least one compressor (11), at least one expansion turbine (14) and a combustion chamber (12) provided with at least one burner (1...
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WO/2015/124909A1 |
A fuel supply system for a gas turbine having at least one combustor (10), comprising at least one first heat exchanger (200A), receiving a fuel from a fuel source at a first temperature through a first fuel line (4) and provide the fuel...
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WO/2015/123820A1 |
A fuel supply line system (200) used for a gas turbine (200), comprising: fuel gas control valves (22, 24) used for controlling delivery to said gas turbine; a first line used for connecting the fuel gas source (10) to said control valve...
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WO/2015/124359A1 |
The invention relates to a method for operating a gas turbine installation (10) with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso). To provide safe operation of the gas tu...
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WO/2015/121035A1 |
The invention relates to a method for operating a compressor train (10) having at least one compressor (12) and at least one cooling device (14) for cooling at least one flow medium (16) to a predefinable compressor temperature (Tcom), i...
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WO/2015/121144A1 |
The invention relates to a method for operating a gas turbine plant (2) having a compressor (12) and a turbine (20), and to an arrangement (42) for controlling a gas turbine plant (2) having a compressor (12)and a turbine (20), and to a ...
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WO/2015/121146A1 |
The invention relates to a method for operating a gas turbine system (2) in part load operation and to an arrangement (48) for controlling a gas turbine system (2) in part load operation, and to a gas turbine system (2) having a compress...
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WO/2015/123107A1 |
The subject matter of this specification can be embodied in, among other things, a fuel pressure regulator system for regulating pressure through a fuel delivery path that includes a fuel pressure regulator valve in the fuel delivery pat...
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WO/2015/121235A1 |
A method (100) of detecting a fault in a bleed air system (20) of an aircraft (10) having multiple engines (12) including transmitting a bleed air flow rate (102) from multiple engines, determining a difference (104) between the transmit...
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WO/2015/122051A1 |
A control device for a power generation system whereby power is generated by a first power source that operates by burning a fuel, wherein the control device identifies, on the basis of a pressure difference in a prior-stage mechanism th...
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WO/2015/119135A1 |
A gas turbine (100) supplies a combustor (103) with fuel and compressed air from a compressor (102) provided with an inlet guide vane (104) in a first part, and rotates a turbine (101) and drives a power generator (150) by means of combu...
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WO/2015/115625A1 |
A gas turbine, a device for controlling the gas turbine, and a method for cooling the gas turbine, wherein the gas turbine has a cooling air supply channel (41) for supplying compressed air bled from a compressor (11) to a disc cavity (3...
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WO/2015/113801A1 |
The invention refers to a method for controlling part load operation of a gas turbine comprising a controller (27) wherein a load set point (LSP) of the controller (27) is greater or equal a minimum load set point (LSPmin).The minimum lo...
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WO/2015/112633A1 |
A gas turbine system (14) includes a fuel control system (264) configured to control a fuel flow to one or more combustors (160) and an oxidant control system (262) configured to control an oxidant flow to each combustor of the one or mo...
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WO/2015/110748A1 |
The invention concerns a turbomachine (1) characterised in that it comprises: - an exhaust housing (7), comprising a plurality of arms (10), the space separating the arms defining openings (13) in which there circulates a primary air flo...
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WO/2015/112317A1 |
A non-transitory, computer readable medium stores instructions executable by a processor of an electronic device. The instructions include instructions to determine that a transient event is occurring in an electrical grid coupled to an ...
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