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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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WO/2023/057714A1 |
The present invention relates to an air-ejector nozzle (6) of a nacelle (1) through which an air flow (F) can pass, the air-ejector nozzle (6) comprising an outer aerodynamic line (61) and an inner aerodynamic line (62) meeting at a trai...
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WO/2023/046426A1 |
The invention relates to a drive device (100) of an underwater transport device (300), comprising at least one tank (130, 140) with a gel-type rocket propellant with at least one fuel gel (132) and an oxidizer gel (142), comprising a fue...
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WO/2023/043437A1 |
A coupling includes first and second housings, a valve element, and a guide link. The first housing is rotatable relative to the second housing. The first housing has helical cam slots and the second housing has linear cam tracks. The gu...
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WO/2023/041881A1 |
One aspect of the invention relates to a hybrid turbomachine comprising a gas turbine engine (10) comprising a high-pressure shaft (8) and a low-pressure shaft (8). The turbomachine further comprising a primary electrical network (UVW), ...
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WO/2023/037075A1 |
Disclosed is an assembly for a turbomachine, comprising: • - a first connection element (9) having a first radial compliance (SRI); • - a second connection element (10) having a second radial compliance (SR2); • - a third connectio...
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WO/2023/037074A1 |
Disclosed is an assembly for a turbomachine comprising: • - a second connection element (8) having a third end (81) which is connected to a turbine shaft (2) and is mounted on a second bearing (5), and a fourth end (82) connected to a ...
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WO/2023/036721A1 |
The present invention relates to shrouded fan engine having an acoustic liner (10) for damping sound waves, comprising a base portion (14) on one side of the acoustic liner (10), wherein the base portion (14) is adapted to attach the aco...
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WO/2023/031550A1 |
The invention relates to a method for manufacturing an acoustic panel (20) comprising a first skin (21), a second skin (22) and an intermediate structure (23) enclosed between these skins (21, 22) and forming oblique cavities (31) with r...
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WO/2023/034291A2 |
The disclosed methods, systems, and kits provide the ability to deliver entire clean sheet designs from concept to first hot fire in under six weeks with instant specific impulses above 330 seconds in some of our engines. In examples, th...
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WO/2023/026014A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, comprising a movable system with deflection cascades (32) and an actuator (52) for moving a movable system (29) between an advanced direct thrust positi...
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WO/2023/026312A1 |
The present invention relates to a propulsion engine mounted on a spacecraft. In particular, the present invention relates to a propulsion engine with which a propellant based on a new concept is selected and loaded for a simple and inex...
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WO/2023/022784A1 |
Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal en...
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WO/2023/014325A1 |
The present invention relates to at least one energy conversion system (1 ) where gas, fuel and air mixture, taken from at least one gas fuel feeding line (20), is burnt in at least one body (10) and where movement energy can be obtained...
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WO/2023/012419A1 |
The invention relates to a bypass turbomachine comprising an exhaust casing (13) traversed by a hot primary flow (FP) and surrounded by a cold secondary flow (FS), and a cone (14) borne by this exhaust casing (13), this exhaust casing (1...
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WO/2023/012559A1 |
An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include...
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WO/2023/012425A1 |
The invention relates to a fan module (1) having variable-pitch blades for a propulsion unit having a longitudinal axis (X), comprising: - a rotary casing (3) carrying the blades (5); - a pitch-changing system (22) comprising a control d...
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WO/2023/008310A1 |
The present invention provides a hybrid rocket fuel combustion method that includes supplying a hydrogen peroxide solution into a combustion chamber provided with a solid fuel, wherein the concentration of hydrogen peroxide in the hydrog...
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WO/2023/001907A1 |
The invention relates to a turbine engine comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downst...
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WO/2023/003490A1 |
The invention relates to the field of aviation, and more particularly to tactical light aircraft having low radar detectability. The technical result consists in increasing the stability and handling properties of an aircraft without neg...
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