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WO/2023/161582A1 |
The invention relates to a turbine engine (1) for an aircraft, which turbine engine has a primary annular flow path (10) and a cold stream duct (20, 30) extending around the primary annular flow path (10), said turbine engine comprising:...
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WO/2023/160876A1 |
The gas turbine system (1) comprises a combustor (3) adapted to combust a fuel and an oxidant and generate pressurized hot combustion gas and a turbine (5) fluidly coupled to the combustor (3) and rotated by expansion of the pressurized ...
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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/2023/155222A1 |
A turbine engine intake gas cooling system and a turbine engine apparatus. A turbine engine is provided with a gas intake end and an exhaust end. The turbine engine intake gas cooling system comprises an intake gas cooling device, which ...
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WO/2023/157520A1 |
This sealing device comprises: a sealing member provided between a rotating part and a stationary part of a rotating machine in a radial direction of the rotating machine; a holding member for supporting the sealing member movably along ...
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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/2023/156741A1 |
The present invention relates to a fuel control system (4) comprising: a fuel source; a supply conduit; a main circuit comprising: a first centrifugal pump; a connecting conduit; a second centrifugal pump; a discharge conduit; and a seco...
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WO/2023/156752A1 |
The invention relates to a sealing system (21) for a turbomachine bearing enclosure (E1), comprising a stator (22) carrying a rotor (23), this system (21) comprising a seal (25) carried by the stator (22) and surrounding the rotor (23), ...
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WO/2023/152108A1 |
The invention relates to a propulsion assembly (1) for an aircraft having at least one propulsion member (10), a gas turbomachine (T) configured to rotate the propulsion member (10), an electric machine (M), mounted downstream of the gas...
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WO/2023/152232A1 |
The invention relates to a heating turbomachine (2) for a fuel-conditioning system (SC), which is configured to supply an aircraft turboshaft engine (T) with fuel (Q) from a cryogenic tank (RC), the heating turbomachine (2) comprising: a...
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WO/2023/148444A1 |
The invention relates to a heat exchanger (21) for a turbomachine, in particular an aircraft turbomachine, having a longitudinal axis (X), comprising: a supporting wall (22) extending in a first direction (L); a plurality of fins (23), e...
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WO/2023/145627A1 |
A gas turbine combustor according to at least one embodiment of the present disclosure is provided with: a combustion cylinder having therein a combustion chamber and having formed therein a plurality of through-holes that open to the co...
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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/2023/139171A1 |
The invention relates to a facility (1) for recovering CO2 from a feed gas flow (FG), including: - a unit (2) for treating the feed gas flow (FG) in order to produce, from the feed gas flow, a CO2-rich gas flow (FCO2) and a nitrogen-rich...
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WO/2023/140180A1 |
A combustor according to at least one embodiment of the present disclosure is a combustor that causes compressed air supplied from a compressor to combust together with fuel. A combustor according to at least one embodiment of the presen...
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WO/2023/138897A1 |
A gas turbine system (1000, 2000, 3000) with a compressor section (10) configured to compress an oxidant flow and to provide a compressed oxidant flow at a combustor section (20). The combustor section (20) is configured to receive the o...
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WO/2023/138906A1 |
A gas turbine system (1000, 2000, 3000) with a compressor section (10) configured to compress an oxidant flow and to provide a compressed oxidant flow at a combustor section (20). The combustor section (20) is configured to receive the o...
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WO/2023/134178A1 |
A gas turbine having an axial force balancing structure, comprising a rotating shaft (100), an air compressor (200), a turbine (300), and a combustion chamber (400). The rotating shaft (100) is provided with a head cone (700), the head c...
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WO/2023/134176A1 |
A gas turbine, comprising a rotating shaft (100), a compressor (200), a turbine (300), and a combustion chamber (400). The compressor (200) and the turbine (300) are sleeved on the rotating shaft (100); a guide vane assembly (600) is pro...
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WO/2023/135378A1 |
The invention relates to a turboshaft engine (1) for an aircraft (2) comprising: - a gas generator (3) comprising a compressor (4), a combustion chamber (5) and an expansion turbine (6); - a power turbine (8) rotating a power take-off (9...
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WO/2023/136314A1 |
A sealing device according to some embodiments comprises: a sealing member that is disposed between a rotating member of a rotating machine and a stationary member disposed on the outer side of the rotating member in the radial direction...
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WO/2023/133073A1 |
A system includes an air cooling system (18) having a heat exchanger (232), a fan (234), and a mount (236). The heat exchanger (232) includes an inlet, an outlet, and a heat exchange conduit (238) between the inlet and the outlet. The in...
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WO/2023/133074A1 |
A method of controlling a fuel blend (26) for a turbine engine (12) is provided. The method includes supplying a first fuel (30) and a second fuel (32) to a mixer (34) and mixing, in the mixer (34), the first and second fuels (30, 32) to...
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WO/2023/132236A1 |
Provided is a turbine static blade composed of a blade body and shrouds respectively formed on both ends in the blade height direction of the blade body. The shroud includes: a main member having a heat-resistance coat film section which...
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WO/2023/127211A1 |
This rotor blade comprises: a blade body extending in a blade height direction that is a direction perpendicular to an airfoil cross-section; and a platform that is provided to an end at a hub side, from between a tip side and the hub si...
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WO/2023/127441A1 |
A gas turbine engine (1) is provided with: a cooling air supply path (41) that supplies air from a compressor (3) as a cooling medium to a turbine (7) while swirling the air in the circumferential direction, the cooling air supply path (...
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WO/2023/126701A1 |
A method for estimating rotor torques (TQmast1, TQmast2,…,TQmastN) of an aircraft (1; 1'; 1'') capable of hovering and comprising a plurality of rotors (31, 32; 33', 34'), which are rotatable under the action of respective rotor torque...
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WO/2023/127718A1 |
This combustor for gas turbines comprises: a shell that is made from metal; a liner that disposed inside the shell and that is made from a ceramic matrix composite material, said liner having an inner surface which defines a combustion c...
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WO/2023/118745A1 |
The invention relates to an assembly for an aircraft turbomachine (2), the assembly comprising: - a nacelle (1) comprising a fixed structure (11, 15, 16) that is suitable for being arranged around the turbomachine (2) comprising an inner...
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WO/2023/118746A1 |
The invention describes an assembly for an aircraft propulsion system (2), comprising: - a nacelle (1) delimiting, together with the propulsion system (2), a fire zone (100, 200); - a fire extinguisher (3) comprising a nozzle (36) for sp...
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WO/2023/118730A1 |
One aspect of the invention relates to a system for cooling a liquid for lubricating an aircraft turbomachine, comprising an exchanger (213) comprising a cooling volume (201) and a circuit (230) for cooling a heat-transfer fluid by a loo...
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WO/2023/118750A1 |
An aircraft turbomachine (10) having a gas generator (12) comprising, along a longitudinal axis (X), at least one compressor (14), a combustion chamber (16) and at least one turbine (18), the turbomachine (10) further having at least one...
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WO/2023/111469A1 |
The present invention relates to an annular air intake lip (40) for a nacelle (3) of an aircraft propulsion assembly (1), the lip (40) extending about an axis of revolution (X) and comprising: - an external annular wall (42), - an intern...
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WO/2023/110701A1 |
The invention relates to an aircraft comprising at least one unducted turbine engine for the propulsion of the aircraft, the turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with ...
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WO/2023/111433A1 |
The invention relates to a turbomachine (10) for an aircraft comprising a stator (16), a turbine shaft (17) and an electric machine (18) arranged to the rear of the turbine shaft, and comprising an electric machine stator (22) and an ele...
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WO/2023/111459A1 |
The invention relates to an oil manifold (18) for a mechanical reduction gear (11) of a turbine engine, which includes a body (19) comprising two opposing side surfaces (20) each configured to extend in part around a planet gear of said ...
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WO/2023/105157A2 |
The invention relates to a method which comprises the following steps: - measuring a pressure difference at terminals of a metering device (22) supplied with fuel by a pump (20); - calculating a position of a valve (24) regulating the pr...
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WO/2023/105938A1 |
The support structure of the present disclosure is a piping support structure that supports piping comprising: a header pipe extending in a first direction within a cross section of a duct and having an inlet formed therein through which...
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WO/2023/105146A1 |
A fuel distribution assembly (11) for a turbomachine, the distribution assembly (11) extending between a first interface plane (P1) and a second interface plane (P2) substantially parallel to the first interface plane (P1), the distribut...
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WO/2023/099559A1 |
Heat exchanger (2) of the air-oil type, for an annular air channel in a turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces for heat exchange with air, said heat exchange zone forming an axi...
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WO/2023/099527A1 |
The invention relates to an axial turbomachine (2), comprising: a first splitter (10) able to separate an incoming air flow (F) into a radially internal air flow (F') and into a radially external air flow, termed secondary flow (F2); a s...
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WO/2023/099533A1 |
Axial turbomachine, comprising: a first splitter nose which can split an incoming air flow into a radially inner air flow and a radially outer air flow, referred to as the secondary flow; a second splitter nose which can split the radial...
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WO/2023/099539A2 |
Disclosed is an axial turbomachine (2) that comprises: a first splitter (10) capable of separating an incoming airflow (F) into a radially internal airflow (F') and a radially external airflow, referred to as secondary flow (F2); a secon...
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WO/2023/099544A1 |
Heat exchanger (2) for an annular air channel in an axial turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces (6) forming a heat exchange passage for air, said heat exchange zone being radia...
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WO/2023/095361A1 |
This gas turbine plant comprises a gas turbine, a liquefaction facility capable of liquefying air, and a liquefaction controller for controlling the liquefaction facility. A compressor has an intake amount adjuster capable of adjusting a...
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WO/2023/094101A1 |
The present invention relates to a system (25) for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system comprising: - at least a first rotary electric machine (26) connected mechanically to the ...
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WO/2023/095721A1 |
A turbine stator vane according to at least one embodiment of the present disclosure comprises an airfoil, an inner shroud provided on the inner-peripheral side of the airfoil, and an outer shroud provided on the outer-peripheral side of...
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WO/2023/088578A1 |
The invention relates to a gas turbine system (100; 310), in particular for operating an electrical generator (320) in an electrically driven motor vehicle (300), comprising at least one gas turbine (102) and at least one control unit (1...
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