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WO/2021/116622A1 |
The present invention relates to an aeronautical propulsion system (1) comprising: - a reduction mechanism (12) coupling a drive shaft (10) and a fan shaft (13) and comprising two reduction stages (27, 32) comprising: a sun gear (33), a ...
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WO/2021/110841A1 |
The invention relates to a space cold gas thruster operating with a solid propellant. The cold gas thruster of the invention comprises a tank (1) suitable for containing a solid propellant and a tank (1) heating device suitable for subli...
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WO/2021/111058A1 |
Aircraft turbine engine (10) comprising: - a gas generator (12) having a longitudinal axis (A), - a fan (14) which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and - an electric mac...
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WO/2021/111061A1 |
Disclosed is an aircraft turbine engine (10), comprising: a gas generator (12) having a longitudinal axis (A), a fan (14) located at an upstream end of the gas generator and configured to turn about said axis, and an electric machine (70...
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WO/2021/108001A1 |
An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity ...
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WO/2021/105595A1 |
The invention relates to a resonating patch (20) for acoustic treatment, comprising a resonant plate (21), a transducer (22) and an electrical circuit (23) electrically connected to the transducer (22), the resonant plate (21) comprising...
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WO/2021/107913A1 |
A catalyst-containing material includes a refractory matrix and particles of one or more catalytic metal elements or catalytic oxides. The particles are dispersed through, and embedded in, the refractory matrix.
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WO/2021/106745A1 |
The present invention relates to resin compositions, fiber reinforced polymeric structures and electromagnetic induction processes for making same. Such magnetic induction processes are pulsed processes that can be optionally coupled wit...
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WO/2021/101568A1 |
A monopropellant thruster according to an exemplary aspect of the present disclosure includes, among other things, a first part having a catalyst bed, a thrust chamber, and a nozzle. The first part is integrally formed via a single addit...
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WO/2021/094094A1 |
The invention relates to an engine assembly (1), in particular for a spacecraft, comprising a drive unit (50) for generating a thrust force, comprising at least one consumer (13) of electrical energy and comprising an energy delivery dev...
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WO/2021/094710A1 |
The invention provides an exhaust nozzle assembly 200 for an air vehicle, comprising an assembly body 202, defining one or more openings 300 for receiving exhaust, and a plurality of nozzles 210a, 210b, 210c, 210d, each nozzle being arra...
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WO/2021/091613A2 |
Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with prebumer and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial prope...
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WO/2021/089935A1 |
Disclosed is a nozzle (1) of a spacecraft engine, comprising a nozzle body (10) extending in a main direction (Z-Z), from a proximal end (12) secured to the spacecraft engine, and a free distal end (14), the nozzle body (10) having a plu...
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WO/2021/084206A1 |
The present invention relates to an acoustic attenuation panel (1) comprising: - a cellular structure (10) comprising a plurality of acoustic cells (100) separated from one another by peripheral partitions (102), - a perforated acoustic ...
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WO/2021/081616A1 |
A segmented augmented turbine assembly for generating electricity from a fluid in motion, the assembly comprising a segmented annular ducted channel extending between an inlet receiving the fluid and an outlet, the channel comprising a c...
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WO/2021/084105A1 |
Provides is an Electric Ducted Fan composed of a Duct (1) within which are mounted: a Stator Hub (3), axially positioned within said Duct (1), onto which are fixed 3 or more Stator Blades (5) which connect said Stator Hub (3) to said Duc...
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WO/2021/086713A1 |
The subject matter of this specification can be embodied in, among other things, an actuator that includes a worm drive assembly having a worm shaft, and a worm wheel configured as a ring having a radially outer perimeter comprising a fi...
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WO/2021/079054A1 |
The invention relates to an aeronautical thrust reverser (20) comprising a sliding cowl (25), shutter flaps (26) and deflection cascades (27). The reverser (20) comprises, for each flap (26), a return member (42) hinged to the sliding co...
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WO/2021/074508A1 |
Counter-rotating turbine (C) for a turbine engine (10), comprising an internal rotor with an inner drum (50a) to which a plurality of internal impellers (22) rotatably supported by a first shaft (26) is attached, an external rotor compri...
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WO/2021/074553A1 |
The present invention relates to a hybrid thruster (100), for a spacecraft or vehicle, comprising an outer body (10), defining a combustion chamber (15) intended for receiving a block of solid propellant (20), a pressurised tank (30) int...
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WO/2021/074513A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion forming an inlet section of...
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WO/2021/074515A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet secti...
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WO/2021/074514A1 |
The invention relates to a propulsion system (1, 1') for an aircraft, in particular a vertical take-off and landing (VTOL) aircraft, comprising a rotor (2) and a nacelle fairing (3) that extends around said rotor in relation to an axis (...
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WO/2021/074521A1 |
The invention relates to a propulsion unit (1) comprising: a gas generator (100) comprising: *a compressor (110), *a combustion chamber (120), *a turbine (130), at least two compressed-air propulsion modules (200), each propulsion module...
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WO/2021/073956A1 |
The invention relates to a vehicle (1) comprising: - a fairing (2); - at least one propeller, characterized in that the fairing (2) defines a fluid chamber having a main opening that opens onto a lower face (22) of the fairing (2) so as ...
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WO/2021/071225A1 |
The present invention relates to an inner composite frame multi-joined barrel, a shell-integrated projectile propellant tank including same, and a method for manufacturing same. The shell-integrated projectile propellant tank of the pres...
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WO/2021/069814A1 |
The invention relates to a propulsion unit (1) for a rocket, comprising a tank (2) designed to contain a propellant, an engine comprising a combustion chamber (3) configured to subject the propellant to combustion generating exhaust gase...
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WO/2021/058330A1 |
The invention relates to a gas turbine engine (10) comprising a transmission (30). The transmission (30) is arranged radially in an interior space (40) delimited by a support structure (24, 24A, 24B, 24C) secured to the housing and provi...
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WO/2021/055065A1 |
An effector health monitor system is configured for coupling with an energetic component. The effector health monitor system includes a characteristic sensor suite including at least first and second characteristic sensors. The first cha...
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WO/2021/048489A1 |
The invention relates to a structural and/or acoustic panel (30) comprising an inner skin (31), an outer skin (32), a honeycomb structure (33) and at least one sealing flange (40). The sealing flange (40) has a U-shaped section directed ...
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WO/2021/048323A1 |
An exterior nozzle member (10) for a turbomachine extending along an axis (X) oriented from upstream to downstream and comprising a primary duct (V1) configured to conduct a primary flow (F1), an annular cavity (16) of axis (X) and a tur...
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WO/2021/044100A1 |
Thrust reverser (10) for a jet engine nacelle (1) comprising means (13; 13'; 13'') for deflecting at least a part of the air flow (F) in the jet engine, and at least one cover (14) that is movable in translation with respect to an extern...
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WO/2021/044096A1 |
The invention relates to a thrust reverser (20) for an aircraft propulsion assembly, this reverser (20) comprising a mobile annular external structure (22), a single actuator (25) for controlling the position of this mobile external stru...
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WO/2021/044099A1 |
The invention concerns an assembly for an aircraft turbomachine, comprising a central gas ejection element (1), and a connection flange (9) interposed between a metal turbomachine outlet (22a) in the upstream direction and the central el...
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WO/2021/044097A1 |
The invention relates to a thrust reverser (20) for an aircraft propulsion assembly, this reverser (20) comprising an outer structure (22) movable between a closed position and an open position of two primary latches (70) configured to l...
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WO/2021/038101A1 |
The invention relates to a method and system for detecting a functional failure in a power gearbox, in particular an epicyclic gearbox (30) in an aircraft gas turbine engine (10) comprising • a) measuring operational data (101) in the ...
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WO/2021/038172A1 |
In a convergent-divergent flap pair (52B) for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap (40B) and the divergent flap (42B) comprise respective cooling air ducts (70, 78) connected to...
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WO/2021/038171A1 |
In a convergent-divergent flap pair (52B) for a turbojet engine nozzle (28) of the variable-geometry convergent-divergent type, the convergent flap (40B) and the divergent flap (42B) comprise respective cooling air circulation ducts (70,...
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WO/2021/038169A1 |
The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air...
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WO/2021/032918A1 |
Internal structure (22) for a nacelle (18) of a turbomachine (10), the structure being designed to surround at least one portion of a compartment capable of receiving a gas generator (14) of the turbomachine (10), the internal structure ...
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WO/2021/032920A1 |
The invention relates to an annular or semi-annular acoustic attenuation structure (200) comprising an inner skin (210) and an outer skin (230), defining between them an annular or semi-annular volume, and a plurality of partitions (220)...
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WO/2021/023947A1 |
The invention relates to a position sensor (18) for an aircraft nacelle thrust reverser door for an aircraft turbojet engine, comprising: - a target (26) to be detected; - a detector (24) having a detection range and comprising a detecti...
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WO/2021/025477A1 |
According to the present invention, an electric pump cycle-liquid rocket engine equipped with a cooling structure for a power transmission part and a method for cooling the power transmission part using same are provided, wherein the pow...
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WO/2021/023934A1 |
The invention relates to a thrust reverser (12) for an aircraft propulsion unit, this reverser (12) comprising a fixed structure (24) and a mobile external structure (16) able to move between a closed position and an open position so as ...
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WO/2021/023935A1 |
The invention relates to a thrust reverser for an aircraft propulsion unit, of the type having a mobile cowl able to move between a closed position that allows the propulsion unit to generate thrust and an open position that allows the p...
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WO/2021/019144A1 |
The invention relates to a turbomachine (10) comprising: - an electric machine (30), - a starter-generator (17) incorporating a second electric machine (40) configured to operate as a starter and a generator, the electric machine and the...
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WO/2021/014085A1 |
The present invention relates to a seal (1) designed to be interposed between a turbojet engine and a movable part of a nacelle, the seal comprising a tubular body (28) delimiting an internal cavity (30) interposed between at least one f...
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WO/2021/008900A1 |
The invention regards a gas turbine engine for an aircraft that comprises a nacelle (112), a fan (102), an engine core located downstream of the fan, the engine core comprising a turbine and a core shaft (111) coupling the turbine to the...
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WO/2021/010810A1 |
A fuel discharge system for a reaction engine having a single-stage or multi-stage dynamic gas compressor is provided with stoichiometric pairs of nozzles and/or tangentially offset pairs of nozzles and/or nozzles for feeding a catalyst ...
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WO/2021/009953A1 |
Provided is a gas turbine system 100 equipped with: a compressor (10) that compresses external air to generate compressed air; a combustor (20) that burns the compressed air generated by the compressor (10) with fuel to generate combusti...
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