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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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WO/2023/001371A1 |
The invention relates to a turbine engine (1) comprising an unshrouded propeller (14) propelling a tertiary flow (13), a fan (12), a compressor (4) compressing a primary flow (F1), and an annular passage (19) for the flow of a secondary ...
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WO/2023/285749A1 |
A method for manufacturing an acoustic attenuation structure (100), comprising the following steps: - producing a complex acoustic multi-element panel (120) comprising a plurality of hollow complex acoustic elements (121) and a plurality...
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WO/2023/281202A1 |
The president document concerns a method for regulating a turbomachine (100) comprising a high-pressure turbine (114) connected to a high-pressure shaft (122) and a low-pressure turbine (115) connected to a low-pressure shaft (121), hot ...
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WO/2023/275836A1 |
Method for manufacturing a core (10) for an aircraft panel (100) with the steps of: arranging first sheet-shaped partitioning elements (12), each with vertical slits (16), extending transversely from a first edge (12a), and transverse sl...
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WO/2023/275839A1 |
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging first sheet-shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first ...
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WO/2023/275454A1 |
The invention relates to a method (200) for controlling a system for generating and controlling power in an aircraft comprising: - a hybrid propulsion system comprising an electrical network and a propulsion-energy source; - at least one...
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WO/2023/278114A1 |
A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a cen...
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WO/2023/275838A1 |
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging a plurality of first sheet- shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transverse...
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WO/2023/274096A1 |
The present invention provides a solid rocket engine rear skirt connection mechanical arm type interstage separation test device and method. The separation test device comprises a front embracing ring assembly, a rear embracing ring asse...
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WO/2023/275473A1 |
The invention relates to a propulsion assembly comprising a shroud defining a flow duct for a secondary flow. This shroud comprises bifurcation panels (19A, 19B, 19C) of which at least one (19C) is hinged to a pylon via connecting member...
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WO/2022/263751A1 |
The invention relates to an acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit (1) in contact with a fluidic flow, the panel (10) comprising a first, acoustically reflective skin (14), a ...
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WO/2022/262998A1 |
The invention relates to a turbomachine (2) of the type having an unducted fan (4), comprising: a splitter (10) separating an air flow (F) into a primary flow (F1) and a secondary flow (F2); a compressor (14) compressing the primary flow...
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WO/2022/263203A1 |
The invention relates to an air inlet (1) of an aircraft propulsion unit (8) comprising thrust reversal means configured to modify a bypass air flow circulating from upstream to downstream in a bypass duct (6) into a reverse air flow (F-...
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WO/2022/264352A1 |
The present invention addresses the problem of providing an injection apparatus for a rocket engine, the injection apparatus being capable of simplifying a structure of an engine nozzle main body portion. A hydrogen injection apparatus...
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WO/2022/259138A1 |
The invention relates to a closed-circuit space shuttle used for interplanetary and interstellar transport and to capturing solar energy, being a constructive combination between rocket and aircraft in which the take-off and landing are ...
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WO/2022/261538A1 |
A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electr...
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WO/2022/254141A1 |
The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure 22 having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position ...
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WO/2022/255956A1 |
The invention relates to a propulsion system for a jet engine an air intake (10); a compressor zone (16) with compressor blades (14) located on a shaft (18) in connection with a fan blade (12); a combustion chamber (20) in which a high-t...
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WO/2022/248790A1 |
This acoustic treatment panel (8; 27; 28) for a jet engine (24) comprises a solid skin (9), a perforated skin (10) and an arrangement of cellular structures (11) sandwiched between the solid skin (9) and the perforated skin (10), the cel...
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WO/2019/021234A9 |
A space propulsion system (1), having reduced sizes, is designed specifically for the application on miniaturised satellites, but it can be scaled easily based upon a wide range of sizes of the target vehicle, and it comprises: a combust...
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WO/2022/243627A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion unit, comprising a fixed structure (31), at least one cowl (33) and a plurality of cascades of deflection vanes (32), the cowl (33) and the cascades of vanes (32)...
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WO/2022/237965A1 |
A vehicle for supersonic or hypersonic flight comprises a thermal rocket engine (lb) with a nozzle (2) and an active cooling system (8). The active cooling system cools a heat shield (6, 7). A working fluid absorbs heat inside the active...
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WO/2022/238664A1 |
The invention relates to a propulsion assembly comprising an actuator (40) connected to an outer casing (11) of a turbomachine by a connecting structure (45). The connecting structure (45) is fastened in line with a structural arm (12) c...
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WO/2022/241438A1 |
The subject matter of this specification can be embodied in, among other things, an engine assembly includes a nacelle configured to at least partially surround an engine, and a thrust reverser coupled to the nacelle, the thrust reverser...
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WO/2022/229556A1 |
The invention relates to a thrust reverser (30) for an aircraft bypass turbojet engine nacelle, this thrust reverser having a generally annular shape around an axis (A) and comprising in particular flaps (10) for deflecting the secondary...
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WO/2022/223915A1 |
A flame-holder device (36) for a turbojet afterburner comprises an annular row of flame-holder arms (38), each having an inner branch (38A) having a free end (50) and another end (52), and two outer branches (38B, 38C) which extend from ...
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WO/2022/222661A1 |
A hypersonic large internal contraction ratio air inlet channel which has a stepless adjustable air release valve, comprising an air inlet channel front body (1), an air-discharging slit cover plate (2) extending backwards from the air i...
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WO/2022/223914A1 |
A diffusion cone (33) for the rear part of a jet engine has a base (50) and, on an opposite side, a truncated tip defining an annular trailing edge (58), and comprises a flame-holder ring (70) with a cross section comprising an external ...
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WO/2022/223916A1 |
The invention relates to a fuel injection device (34) for a turbojet engine afterburner, comprising a base (80), a fuel tube (40) provided with fuel ejection ports (44), an air tube (50) provided with cooling air passage ports (54), and ...
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WO/2022/223929A1 |
The invention relates to a thrust reverser (20) comprising doors (40), a rear shell ring (50, 51) and an actuation system (60, 62, 63) for synchronizing the pivoting of the doors (40) and the translation of the rear shell ring (50, 51).
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WO/2022/223904A1 |
The invention relates to a thrust reverser device for an aircraft turbojet engine nacelle, having an electro-hydrostatic actuation system, the electro-hydrostatic system comprising a motor pump (106) and a first actuation assembly (E) fo...
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