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WO/2022/212059A1 |
Embodiments of a fuel system are disclosed. The fuel system includes a bypass valve (BPV), a fuel metering valve (FMV), a flow sense valve (FSV), and an actuator regulating valve (ARV). The BPV includes a BPV valve member that regulates ...
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WO/2022/209562A1 |
A gas turbine system 1 is provided with: an ammonia tank 14; a combustor 13 that is connected to the ammonia tank 14 and that has a combustion chamber 13a; a suction flow channel 41 that is connected to the combustor 13; a compressor 11a...
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WO/2022/209563A1 |
A gas turbine system 1 comprising: an ammonia tank 14; a combustor 13 connected to the ammonia tank 14; an exhaust flow path 42 connected to the combustor 13; a turbine 11b provided in the exhaust flow path 42; a decomposed gas reservoir...
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WO/2022/202862A1 |
The present invention provides a gas turbine system and a method for controlling the same, the gas turbine system comprising: a gas turbine that includes a compressor which generates compressed air, a combustor which combusts fuel with t...
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WO/2022/202818A1 |
This gas turbine comprises: a compressor that generates compressed air; a combustor that combusts fuel using the compressed air; and a turbine that is driven by a combustion gas generated by the combustion of fuel in the combustor. The g...
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WO/2022/195224A1 |
The invention relates to a system (400) for pumping and metering a fluid (10) for a turbine engine, which system comprises at least one pump (412, 414) for the fluid and an electronic computer (430) configured to determine the flow rate ...
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WO/2022/189154A1 |
Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger...
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WO/2022/182092A1 |
The present invention comprises: a turbine part which is connected to a plurality of energy consumers located in an industrial estate; a compressed air supply part which is provided in the turbine part and provides compressed air to the ...
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WO/2022/172955A1 |
This fuel supply equipment comprises: a main ammonia line through which liquid ammonia flows; a vaporizer which is connected to an end of the main ammonia line, and which performs heat exchange between a heating medium and the liquid amm...
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WO/2022/162306A1 |
The invention relates to a system (27) for controlling discharge doors (26a-26f) of a turbomachine, said system comprising a ring (28) and means for connecting this ring (28) to each discharge door (26a-26f). According to the invention, ...
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WO/2022/149540A1 |
A gas turbine combustor according to at least one embodiment of the present invention comprises: a low combustible fuel flow adjuster for independently adjusting the amounts of low combustible fuel to be supplied to a first fuel injector...
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WO/2022/121267A1 |
A gas turbine fault monitoring system and method. The system comprises a detection module (101), a fault level determining module (102), a control module (103), and a fault response execution module (104). The detection module (101) dete...
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WO/2022/117465A1 |
A method of controlling a combustor of a gas turbine engine, the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fu...
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WO/2022/117464A1 |
A method of controlling a combustor of a gas turbine engine is disclosed. The method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split in...
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WO/2022/112028A1 |
The invention relates to a method for controlling a turbine engine comprising an electric motor forming a device for injecting torque on the high-pressure rotation shaft, in which method a setpoint for fuel flow into the combustion chamb...
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WO/2022/112713A1 |
The invention relates to an actuating device (12) of a fuel pump (20) for an aircraft engine (18), the actuating device (12) comprising a motor (24), a generator (26) and an electrical connection member (27), the motor (24) being an asyn...
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WO/2022/111577A1 |
A bypass auxiliary system for a closed Brayton cycle heat engine system. The bypass auxiliary system comprises a first regulation unit and a second regulation unit, the first regulation unit comprising a first branch pipeline (30), a com...
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WO/2022/105212A1 |
A gas-blown miniature gas turbine, comprises a gas compressor (1), a turbine (2), a rotating shaft (3), a gas inlet channel (4), and a combustion chamber (5). The gas compressor (1) and the turbine (2) are sleeved on the front end and ta...
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WO/2022/099955A1 |
The present invention provides a method for keeping combustion of a gas turbine stable in a dynamic process, a computer readable medium, and a gas turbine control system. The method comprises: compensating for a fuel control valve stroke...
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WO/2022/096815A1 |
Disclosed is an aircraft dual-flow turbine engine assembly (32) comprising: • - an internal shroud (42) for externally delimiting a primary flow path (16) of the turbine engine gases; • - an external shroud (40) for internally delimi...
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WO/2022/096354A1 |
The invention relates to a method for determining an efficiency fault (R11-R15) of at least one module (11-15) of a turboshaft engine (T) of an aircraft (A), the method for determining comprising: • A step of determining an estimated r...
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WO/2022/091899A1 |
This combustion adjustment method applied to the combustion control of a combustor executes a first step for selecting a combustion parameter for a load of a gas turbine and increasing or decreasing a command value of the combustion para...
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WO/2022/091504A1 |
An output corrector is provided with an adjustment coefficient creating unit which creates an adjustment coefficient, an output adjusting unit which adjusts a control output using the adjustment coefficient, and an output accepting unit ...
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WO/2022/092008A1 |
This device for analyzing the composition of fuel gas containing inert gas and flammable gas comprises a heating value measurement device that measures a heating value per unit amount of the fuel gas, a density measurement device that me...
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WO/2022/091505A1 |
A maximum output creator is provided with: a temperature reception unit that receives an intake temperature, which is the temperature of air taken in by a compressor of a gas turbine; a change reception unit that receives the details of ...
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WO/2022/084614A1 |
The invention relates to a turbojet engine (10) comprising successively, from upstream to downstream in the direction of flow of a primary air stream, a low-pressure casing (12), an intermediate casing (14) and a high-pressure casing (16...
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WO/2022/079523A1 |
An adjustable injector system (100) for adjusting a radial distribution of a mixed fuel (117) includes an adjustable injector (110) configured to receive first and second non-carbon fuels (112, 114) and configured to adjust the radial di...
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WO/2022/079435A1 |
An aircraft (101) comprising: one or more main engines (104a, 104b); a first fuel in a first fuel tank (111a) configured to be fed towards at least one of the one or more main engines through a first fuel line; and a second fuel differen...
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WO/2022/069828A1 |
The invention relates to an actuating device (22) for actuating a pump (20) of a pumping system (12) for pumping the fuel of an engine (18), comprising a motor (24), a generator (26), an inverter (28), a switching member (30) and a contr...
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WO/2022/066471A1 |
A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes ...
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WO/2022/061871A1 |
A hybrid-adaptive differential evolution-based iterative algorithm for an aeroengine model, comprising the following steps: establishing an aeroengine component-level model; solving an engine model by means of a hybrid-adaptive different...
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WO/2022/049335A1 |
The invention relates to an assembly (10) for storing cryogenized fuel, comprising - a reservoir (12) in which fuel is present in liquid form and in gaseous form, the gaseous form resulting from the evaporation of the fuel in liquid form...
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WO/2022/042883A1 |
A hybrid gearbox for a mechanical driven equipment in a train system is disclosed. The hybrid gearbox is connected between a power source and a load, to be driven. The hybrid gearbox includes a layshaft gear, capable of adjusting the tra...
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WO/2022/042884A1 |
A method of operating a train system for driving a mechanical driven equipment is disclosed. The train system comprises a hybrid gearbox connected between a power source and a load to be driven. The hybrid gearbox includes a lay shaft ge...
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WO/2022/042885A1 |
A method of operating a train system for driving a mechanical driven equipment is disclosed. The train system comprises a hybrid gearbox connected between a power source and a load to be driven. The hybrid gearbox includes a lay shaft ge...
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WO/2022/040497A1 |
A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionall...
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WO/2022/034083A1 |
Method and system for controlling the thrust of an aircraft turbomachine (100) having a high bypass ratio by direct action on a variable-pitch system (123) for varying the pitch of the vanes of a stator (121) of a low-pressure compressor...
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WO/2022/005367A1 |
A method and a controller (101) is disclosed for controlling rotational speed of a turbine (122) in a turbine system (105). The turbine system (105) comprising the turbine (122), a pressure sensor (130), a filter (132) and a drive unit (...
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WO/2022/003540A1 |
The present disclosure provides methods for controlling volumetric flows of streams into a combustor (10a), and particularly in a combustor utilized in a power production method. A controller (210) can be used to receive a variety of inp...
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WO/2022/002436A1 |
A method for monitoring and controlling a hybrid gas turbine system is disclosed, which is performed by a control logic unit. The method is implemented by executing an optimization among operating variables, so as to obtain control signa...
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WO/2022/004237A1 |
A CAES generation device is provided with: a plurality of motors 15; compressors 11-14 driven by each of the plurality of motors 15 and fluidly connected in multiple stages; an accumulation pressure tank 30 which accumulates compressed a...
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WO/2021/262853A1 |
The subject matter of this specification can be embodied in, among other things, a method that includes igniting an igniter stage configured to ignite combustion in a turbine combustor assembly, receiving pressure signals from a pressure...
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WO/2021/260173A1 |
A gas turbine engine comprising at least one radially extending bleed passage optionally in fluid communication with at least one generally circumferentially extending plenum. The passage has an upstream inlet in fluid communication with...
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WO/2021/257045A1 |
The invention relates to aviation technology and is intended for use as a power plant in both supersonic and subsonic passenger aircraft. Owing to the design of the claimed pure turbojet engine, when an aircraft is flying at supersonic s...
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WO/2021/257239A1 |
Embodiments of the disclosure provide a method for controlling a power plant (100). The method may include detecting a transient load on the power plant (100), and monitoring a system reactance during operation at the transient load. A s...
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WO/2021/240485A1 |
A method for detecting blowout precursors in at least one gas turbine combustor comprising: receiving combustion dynamics acoustic data measured by an acoustic measuring device associated with the combustor in real time; performing wavel...
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WO/2021/214402A1 |
The invention relates to a turbine engine (1) wherein an inlet flow (F) is separated into a first stream (Fp) flowing through a first vein (16) and a second stream (Fs) flowing through a second vein (17), and comprising a gas generator (...
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WO/2021/206884A1 |
Fuel isolation systems, apparatuses and methods are described. In some embodiments, a system comprises a fuel tank, a fuel pump, an engine, a firewall, a fuel line from the fuel tank to the engine, a connector coupled inline with the fue...
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WO/2021/197977A1 |
The present application provides a steam turbine (100) with a flow of steam therethrough. The turbine (100) includes a first guide blade (210), a second guide blade (220), a flow path (275) for the flow of steam therebetween, and a fluid...
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WO/2020/170227A9 |
A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces...
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