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WO/2023/171681A1 |
A rotating detonation engine comprising: an outer cylinder that extends in an axial direction; a base that is connected to the outer cylinder, and comprises a plurality of fuel injection ports positioned in a circular ring shape and inje...
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WO/2023/171549A1 |
The present invention relates to a pump system and an engine system. Provided is a pump system (PS) appliable to an engine system (ES) mounted in a space navigation body. The pump system (PS) is provided with: a motor (M); a first pump (...
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WO/2023/166266A1 |
The present document relates to an exhaust cone for an aircraft turbine engine, extending along a longitudinal axis (X), said cone comprising a radially inner annular wall (104) and a radially outer skin (102) delimiting a flow path for ...
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WO/2023/166273A1 |
A device (20) for supporting a fluid duct (C), comprising: - a link (22) for supporting the duct via two end parts (22a) of the link that are spaced apart from one another in a longitudinal direction and adopting, transversely, a curved ...
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WO/2023/166534A1 |
Think above the speed of sound and engineering which breaks that barrier of sound speed and gives us supersonic and hypersonic speeds many cruise missiles and air-to-air missiles work on supersonic speed mostly between Mach 2.5 to Mach 4...
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WO/2023/161586A1 |
The present invention relates to an aircraft engine assembly comprising: a duct (4); a beam (51); and an acoustic fairing.
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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/2023/163616A1 |
The invention relates to engine design, and more particularly to an operating method and an arrangement for mass expulsion nozzles for various engines. Said arrangement consists in a nozzle that is notionally divided into two parts (defi...
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WO/2023/156760A1 |
The present invention relates to an exhaust nozzle for fluidic-thrust vectoring, comprising an elongate channel for directing exhaust gasses having first and second ends. The elongate channel has an inlet at the first end comprising a co...
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WO/2023/152443A1 |
Valve designed for large flow rates and high pressures, and a rocket engine comprising such a valve, the valve comprising a valve body (11), having a first path (I) and a second path (II), a movable shut-off member (40) configured to adj...
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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/2023/152005A2 |
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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/2023/148449A1 |
The invention relates to a propulsion assembly for an aircraft equipped with a thrust reverser comprising an actuator (52) for moving a movable structure (29) between an advanced direct thrust position and a retracted thrust reversal pos...
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WO/2023/137255A1 |
An effector having an extendible range and a method for extending the range of an effector includes using an axially translatable center body that is movable from a stowed position, in which the center body is stowed in an outer body of ...
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WO/2023/131761A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, comprising a fixed structure (31) equipped with at least one cascade (32) as well as a radially inner delimiting wall (18) of a secondary vein (21B), an...
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WO/2023/131762A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, comprising at least one sealing membrane (58) designed to deflect at least one portion of the secondary flow towards a set of cascades (32') when the mo...
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WO/2023/118686A1 |
The invention relates to a turbine engine module, comprising: - a fan (3) intended to be rotated by a fan shaft (32) and comprising a plurality of variable-pitch blades (30); and - a pitch change system comprising a control means (52) co...
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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/2023/118743A1 |
A system for conditioning fuel for an air-breathing hydrogen engine (M), comprising: • - at least one hydrogen pump (16) configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, • - one or more he...
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WO/2023/118690A1 |
The invention relates to a tool (30) for moulding a duct for an aircraft turbine engine, the duct being made of a fibre-based composite material and comprising a curved tubular portion, one end of which is connected to a peripheral flang...
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WO/2023/111424A1 |
Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annul...
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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/2023/113628A1 |
The subject of the invention is a laboratory stand for studying the effect of accelerations on the linear burning rate of solid rocket propellants. The laboratory stand for studying the effect of accelerations on the linear burning rate ...
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WO/2023/108306A1 |
The invention relates to a gas turbine engine for aircraft propulsion and to a method for operating same. A gas turbine engine FIG. 1 is presented which consists both of a low-pressure compressor (KN), a high-pressure compressor (KH), a ...
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WO/2023/103398A1 |
An air compression acting device, comprising an inner casing (18) and a main shaft (1) axially arranged in the inner casing (18) in a penetrating manner, an intake turbine (4) and a screw-type air compressor (6) being sequentially arrang...
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WO/2023/107497A2 |
A fuel grain for a hybrid rocket engine includes multiple layers of fuel grain material defining a combustion port extending through a body of the fuel grain, in which each layer includes multiple beads of fuel grain material, in which t...
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WO/2023/099851A1 |
An assembly (10) for an exhaust cone of an aircraft turbomachine, comprising a first annular wall (11), and first partitions (12) and second partitions (13) defining between them a plurality of acoustic boxes (21) distributed around the ...
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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/2023/099852A1 |
The invention relates to an assembly (10) for an ejection cone of an aircraft turbomachine, comprising a first annular wall (11) and a plurality of first partitions (12) and of second partitions (13) extending substantially perpendicular...
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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/2023/094101A1 |
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/2023/091123A1 |
A novel gas propulsion device comprises one or more high-frequency linear actuators (such as a voice coil linear actuator or a piezoelectric linear actuator) attached to one or more gas propulsion elements having a concave internal surfa...
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WO/2023/091583A1 |
An enclosure for an aircraft powerplant includes an air inlet, an air outlet, and at least one sidewall forming the enclosure and fluidly connecting the air inlet and the air outlet. The enclosure further includes a cavity configured to ...
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WO/2023/089267A1 |
The invention relates to a method for producing a component comprising a plurality of hollow complex elements, including: - filling a plurality of molding cavities (111) with a thermoplastic material (6), the mold (100) being maintained ...
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WO/2023/079233A1 |
The invention relates to an acoustic attenuation structure (100) comprising a lower multicellular structure (130) and an upper multicellular structure (110), at least some of the cells (112) of the upper multicellular structure (110) at ...
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WO/2023/079024A1 |
The invention relates to an impeller machine with an aero rotor (14) for generating an air flow along an annular space (31) enclosed between an impeller housing (15) and a motor housing (19). The motor housing (19) is arranged in an inne...
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WO/2023/077064A1 |
A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the dire...
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WO/2023/073305A1 |
Turbomachine (100) comprising a fan (120) arranged along a longitudinal axis (X) of the turbomachine, a primary duct (130) able to channel a primary air flow of the fan through a compressor, a combustion chamber and a turbine of the turb...
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WO/2023/070891A1 |
The present invention relates to the technical field of hydrogen fuel power generation, and relates specifically to a hydrogen fuel high-speed rotating magnetofluid power generation device. The device comprises a shaft portion, a cover p...
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WO/2023/072344A1 |
The invention relates to an aircraft engine for commercial aircraft. The problem to be solved by the invention is that of providing an aircraft engine having a fuel-cell-based, electrically operated axial-flow fan which, according to the...
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WO/2023/073306A1 |
A method for detecting the presence of a crosswind for a turbomachine of an aircraft comprising at least two turbomachines arranged on either side of a main axis of the aircraft, each of said turbomachines comprising a low-pressure shaft...
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WO/2023/067252A1 |
The invention relates to a method (100) for correcting the thrust vector created by a thrust assembly associated with electrical means for correcting said thrust vector. Such a thrust assembly comprises a mechanical rotor rotated by a ro...
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WO/2023/064215A1 |
An ejector nozzles for an aircraft can include ducts that transition axially from a first cross-sectional shape, to a second cross-sectional shape that is geometrically non-similar or dissimilar to the first shape. In representative embo...
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WO/2023/062329A1 |
Rear assembly for a turbojet engine nacelle, comprising at least one composite wall (20) separating a cold portion (8) from a hot portion (12) comprising an element to be cooled (23), the composite wall (20) comprising first and second s...
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WO/2023/059410A2 |
Supersonic jet engine includes a housing and an exhaust nozzle. Spike extends outwardly from the housing. Plurality of fans are arranged in an axial direction within the housing, each of the plurality of fans includes a plurality of fan ...
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WO/2023/057704A1 |
The invention relates to an outlet nozzle (12') for an aeronautical thruster arranged downstream of at least one stator vane (32) of the thruster, a trailing edge (122') of the outlet nozzle comprising a plurality of chevrons (4) distrib...
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