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WO/2024/095638A1 |
A gas turbine system 100 comprises: an ammonia supply source 1; a gas turbine 4 including a combustor 42 that is connected to the ammonia supply source 1 and that burns ammonia from the ammonia supply source 1; a water electrolysis devic...
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WO/2024/095848A1 |
This control device controls a gas turbine combustor capable of burning fuel gas and air mixed together inside a combustion chamber with a burner. The burner is provided with a first fuel gas injection hole, a second fuel gas injection h...
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WO/2024/096885A1 |
A system is provided with a bypass system having a first valve, a first drive coupled to the first valve, and a controller coupled to the first drive. The controller is configured to operate the first drive to move the first valve betwee...
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WO/2024/095121A1 |
Disclosed herein is a method for controlling instability in a combustion chamber of a gas turbine. This method is done by changing in flow rate of channels of the combustion chamber in the form of reducing a certain amount of flow rate i...
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WO/2024/090524A1 |
This hybrid rotor drive system comprises: a gas turbine engine which includes a compressor, a combustor, a turbine, and a first output shaft mechanically connecting the compressor to the turbine; an electric motor including a second outp...
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WO/2024/090092A1 |
This combustion system (100) is provided with: an ammonia supply source (1); a cracking device (3) which is connected to the ammonia supply source (1) and decomposes ammonia into hydrogen and nitrogen; a combustor (42) which is connected...
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WO/2024/084160A1 |
The invention relates to a turbojet engine comprising: a combustion chamber and a jet pipe; a main circuit (11) including a main centrifugal pump (14) and a main positive displacement pump (16) supplying fuel to the injectors (18) of the...
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WO/2024/084168A1 |
The invention relates to a device (B) for regulating a system (A) for supplying hydrogen to a turbine engine comprising a combustion chamber, the hydrogen supply system comprising, in particular arranged in series, at least: - a pressuri...
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WO/2024/084922A1 |
This gas turbine control device controls a gas turbine comprising a combustor capable of generating combustion gas for driving the gas turbine by cofiring a first fuel and a second fuel. When it is determined that the supply of the secon...
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WO/2024/083502A1 |
The invention relates to a fuel conditioning system (SC) configured to power an aircraft turbomachine (M) with fuel (Q) from a cryogenic tank (R), the conditioning system (SC) comprising: a fuel circuit (1); a distribution valve (5) conf...
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WO/2024/078930A1 |
A fuel conditioning system (SC) configured to supply an aircraft turbine engine with fuel (Q) coming from a cryogenic tank (R), the conditioning system (SC) comprising: a fuel circuit (1); a first heat module (31) mounted in an aircraft ...
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WO/2024/061558A1 |
A gas turbine engine has a core flow path and an outer flow path, the outer flow path positioned at a greater radial displacement from a rotational axis of the engine than the core flow path. The gas turbine engine also has a cavity to p...
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WO/2024/064270A1 |
An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that ...
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WO/2024/064620A1 |
Disclosed is a method enabling operation of a combustion system with at least two serially arranged combustion zones on fuels generally yielding varying flame speeds. First, the operating parameters of the gas turbine engine are determin...
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WO/2024/056929A1 |
The present invention relates to a smart device (100) for supplying ammonia and hydrogen for mixed combustion in aircraft, as shown in Figure 1, for propulsion. The smart device comprises a subassembly (120) that stores ammonia and suppl...
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WO/2024/054295A1 |
A flow system (10) includes a flow source device (12) configured to receive fluid from a first flow line (14) and output fluid on a second flow line (16). An output (18) is in fluid communication with the flow source device on the second...
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WO/2024/054836A1 |
A dual-fuel turbine engine is a type of turbine engine that can operate using two different fuel sources, such as liquid fuel (e.g., diesel) and natural gas. For liquid fuels, the turbine engine includes a primary line to facilitate engi...
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WO/2024/028553A1 |
The invention relates to a turboprop (10) comprising: - a turbine (12) mechanically connected to an input (21) of a reducer (20); - a tail shaft (30) bearing a variable-pitch propeller (31); - a rotary electric machine (46); and - an ele...
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WO/2024/023439A1 |
The invention relates to an electrical power generation and distribution system 1 for a hybrid-electric propulsion aircraft powered by at least one turbojet engine (10). The system comprises at least N ≧ 2 (N integer) distribution netw...
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WO/2024/013462A1 |
The present invention relates to a method and system for managing the drawing of mechanical power from a two-spool or three-spool turbine engine (1) for an aircraft, in which at least two electric machines (3, 4) are suitable for recover...
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WO/2024/009715A1 |
A gas turbine system (1), including a gas turbine engine (3) having a compressor (11), a combustor (13), and a turbine (15), and a fuel gas pressure adjustment device (5) that adjusts the pressure of the fuel gas (F) introduced into the ...
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WO/2024/009755A1 |
This gas turbine control device is a control device for controlling the operation of a gas turbine, and comprises a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine, and a speed incr...
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WO/2024/006185A1 |
A redundant fuel metering system and method for a multi-stage combustor that utilizes a fuel metering valve EHSV from a less critical combustor stage fuel metering system as a redundant backup to the main metering valve EHSV. In the even...
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WO/2024/002517A1 |
An online rotor thrust adjustment system is disclosed. The online rotor thrust adjustment system comprises at least an axial thrust balance flow net (16) between a compressor (12) and an expander (11) of a gas turbine, the axial thrust b...
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WO/2023/243358A1 |
This gas turbine control device is provided with a frequency analysis unit, a database, a combustion state prediction unit, and a correction amount calculation unit. The frequency analysis unit performs a frequency analysis of the vibrat...
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WO/2023/233097A1 |
Propulsion assembly (100) for an aircraft, in particular a multi-engine helicopter, comprising at least a first engine (1) and a second engine (2) that are configured to operate in at least one standby mode, a primary air-circulation dev...
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WO/2023/218930A1 |
This gas turbine control device comprises: a fuel flow rate calculation unit that calculates a fuel flow rate indicating an amount of fuel entering a combustor; an air flow rate calculation unit that calculates an air flow rate indicatin...
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WO/2023/217798A1 |
The invention relates to a method for controlling a turbomachine comprising a fan positioned upstream of a gas generator, the turbomachine comprising an electric motor forming a torque injection device for a high-pressure rotary shaft, i...
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WO/2023/208459A1 |
The invention relates to a method for operating a multi-stage air compression system (1), comprising an electrically driven first compressor (1.1) and a second compressor (1.2) which is driven by means of a turbine (2), wherein the compr...
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WO/2023/204096A1 |
A gas turbine control device of the present disclosure controls a gas turbine in which a combustor is configured in a state where a plurality of fuel supply nozzles for supplying fuel are separated into a first group and a second group. ...
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WO/2023/198329A1 |
Method of operating a gas turbine (GT), wherein a compressor for the gas turbine (GT) has adjustable guide vanes (IGV) at the inlet of the compressor, wherein the compressed air by the compressor is mixed with fuel in order to burn the m...
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WO/2023/197458A1 |
A gas turbine system coupled with an energy storage system and having an adjustable compression flow, and a control method. The system comprises a high-pressure gas storage system, a heat exchange system, a comprehensive gas supply syste...
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WO/2023/194665A1 |
The invention relates to a gas turbine (110) comprising - two unducted propellers; - a main duct (171); - at least one compression stage (145) located in the main duct (171); - a cooling duct (173) extending from a cooling inlet and open...
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WO/2023/181513A1 |
A combustion system (1) comprises: a combustor (12) including a first combustion region (12a) and a second combustion region (12b) continuous with the first combustion region (12a) on a downstream side; a first burner (13) including an i...
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WO/2023/181512A1 |
A combustion system 1 comprises an ammonia tank 14, a combustor 12 connected to the ammonia tank 14, an intake flow path 101 connected to the combustor 12, a compressor 11a provided in the intake flow path 101, an ammonia recovery tub 16...
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WO/2023/181616A1 |
A device for controlling gas turbine equipment comprises: a combustion load command generator that determines a combustion load command value, which is a parameter having a positive correlation with an inlet temperature, which is the tem...
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WO/2023/179911A1 |
A firing apparatus to control the firing of one or more burners of a gas turbine is disclosed. The firing apparatus comprises a shutoff module, for selectively allowing the passage of the fuel from a fuel source, and an adjustment module...
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WO/2023/175260A1 |
Dismountable aeronautical pod device 30 with cryogenic storage capacity, for external transportation by an aircraft, comprising a front cryogenic tank 36, a rear cryogenic tank 37, and at least one central temporary storage tank for the ...
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WO/2023/175261A1 |
Aeronautical device 1 for distributing gas in an aircraft between at least one source 2 of liquefied gas and at least one gas consumer member 3, comprising at least one first controlled all-or-nothing valve 11 at the output of each sourc...
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WO/2023/175270A1 |
The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises a gas turbine engine (200) and at least one electric machine (300, 400) which is mechanically coupled to a rotating shaf...
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WO/2023/170358A1 |
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each down...
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WO/2023/162375A1 |
A combustion device comprises a plurality of burners to which ammonia and second fuel are supplied, and a control device. The control device is configured such that in a first load region S1 including zero load, the control device suppli...
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WO/2023/158807A1 |
Gas turbine combustor assembly (100) comprising a primary combustion chamber (106) in fluid communication with a primary fuel injector and a primary air inlet, and an igniter (200) carried by the primary combustion chamber an including a...
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WO/2023/156074A1 |
A simulation method for simulating the operation of a gas turbine (111) is disclosed. The method comprises a global search procedure and an iterative local search procedure, to calculate parameters to simulate the operation of the gas tu...
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WO/2023/155039A1 |
A dual-fuel power system and an air supply and purge method therefor. The dual-fuel power system comprises a plurality of dual-fuel power devices, a first air compressor and a second air compressor. Each of the plurality of dual-fuel pow...
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WO/2023/151152A1 |
The present disclosure relates to a multi-fuel switch device and method used for a gas turbine and a gas turbine. The device comprises a gas fuel pipeline, a liquid fuel pipeline, a purge fluid first pipeline, a purge fluid second pipeli...
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WO/2023/148439A1 |
The invention relates to a method for braking an aircraft turbine engine including a fan (6) or a propeller connected to a turbine (5) by a shaft (7), and an electric generator (9) connected to the shaft (7), the method comprising the fo...
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WO/2023/140183A1 |
At least one embodiment of the present disclosure relates to a control method for a gas turbine combustor comprising an air-hole plate having a plurality of air holes formed therein, and a plurality of fuel nozzles corresponding to respe...
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WO/2023/140045A1 |
A gas turbine control device according to at least one embodiment of the present disclosure comprises a purge gas flow rate control unit that controls the flow rate of purge gas for discharging fuel gas remaining inside the gas turbine t...
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WO/2023/139295A1 |
The invention relates to a method for reducing the negative environmental effect of the contrails emitted by an aircraft (100), which comprises the following steps: obtaining the atmospheric conditions outside the aircraft (100) and, if ...
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