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WO/2021/188660A1 |
An apparatus for testing a liquid propelled rocket and associated method comprising a housing, a load cell assembly, a launcher assembly, a rocket assembly, and a base piston; the load cell assembly, the launcher assembly, the rocket ass...
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WO/2021/184085A1 |
A device for passively reversing a flow of pressurized fluid and capturing the impulse thereof does not comprise movable parts and is disposed as a passive element at the outlet of an external power device that generates reactive thrust,...
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WO/2021/180509A1 |
An air outlet (4) for a nacelle (2) for an aircraft turbofan (T) comprising an inner wall (41) and an outer wall (42) connected to each other by a trailing edge (43), at least one radial through aperture (44) extending over an angular po...
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WO/2020/208318A9 |
The invention concerns a hybrid propulsion installation (100) for an aircraft, comprising: an internal combustion engine comprising at least one combustion chamber (114); at least one electricity generator (134a, 134n); an electrical pro...
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WO/2021/181031A1 |
The invention relates to a fan module (100) for an aircraft turbomachine (10), comprising: - a fan (14) comprising a disc (32a) carrying fan blades (30), - a rotor (62a) of an electric machine (62), this rotor (62a) having an annular gen...
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WO/2021/181401A1 |
A launch system is provided, including a composite vehicle and a carrier vehicle. The composite vehicle includes a payload vehicle, a booster vehicle and a first coupling system. The payload vehicle is configured for powered spaceflight ...
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WO/2021/176182A1 |
The invention relates to a method for manufacturing a structure with cellular cores comprising at least one cell which comprises a secondary duct having a first end (24) defining a sound wave input, and an opposing second end (24'), the ...
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WO/2021/176152A1 |
The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured...
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WO/2021/170932A1 |
The invention relates to a thrust reverser comprising an acoustically treated deflection edge. The present invention relates to a thrust reverser (1) for a jet engine nacelle, equipped with a front frame (2) comprising a support (20) whi...
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WO/2021/171988A1 |
This combustion apparatus (C) for a rocket engine is equipped with: a combustion chamber for causing a combustion reaction between a fuel and an oxidant; injectors (3A, 3B) for injecting the fuel and the oxidant into the combustion chamb...
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WO/2021/170934A1 |
The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the ...
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WO/2021/164549A1 |
An electric energy-driven jet aircraft engine, comprising a jet core engine (3) comprising a gas compressor (31) and an accelerator (32) which are sequentially arranged in a gas inlet direction, wherein the gas compressor (31) is used fo...
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WO/2021/165606A1 |
Dual flow turbine engine (10) comprising: - at least one lubricant tank (40) located in an annular space of the turbine engine body, - at least one hatch (46) which is provided on an external cowling (32) of a nacelle, for filling the ta...
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WO/2021/162091A1 |
A gas turbine engine according to an embodiment of the present invention is provided with an oil tank for storing lubricating oil, a compressor, a combustor, and a cylindrical external case accommodating a turbine, wherein the oil tank i...
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WO/2021/161873A1 |
This propulsion device comprises a gas generator and a plurality of thrusters. The gas generator generates combustion gas when a flying object satisfies emergency conditions. Here, the plurality of thrusters output the combustion gas dow...
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WO/2021/160952A1 |
An electrical assembly for an aeronautical turbine engine, comprising an electric machine (70) configured to be disposed in a turbine engine (100) and comprising a stator (72) and a rotor (71) comprising magnets, the assembly comprising ...
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WO/2021/160953A1 |
One aspect of the invention relates to a method for controlling a turbojet thrust reverser during an aborted aircraft takeoff, the thrust reverser comprising: - doors that can move between a closed position, an over-closed position and a...
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WO/2021/157567A1 |
Provided are a spacecraft liquid propulsion system failure diagnosis system that can reliably diagnose a failure of a spacecraft, and a spacecraft liquid propulsion system failure diagnosis method. The spacecraft liquid propulsion system...
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WO/2021/156036A1 |
Disclosed is an air outlet (4) of a nacelle (2) for an aircraft turbojet engine, the nacelle (2) forming a solid of revolution about a longitudinal axis (X), the air outlet (4) comprising a straightening device (9) comprising a plurality...
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WO/2021/156477A1 |
This device for attaching a connecting rod small end (10) for a thrust reversal cascade flap onto a fixed internal structure (11) of a turbojet engine (3) nacelle (2) comprises a fitting (13) that is suitable for being fixed to the inter...
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WO/2021/156561A1 |
The present disclosure relates to a method for refrigerating a cryogenic fluid supply circuit (3), comprising a step (E1) of acquiring a value (T°c) for the state of the cryogenic fluid supply circuit (3) at a current time (tc), a step ...
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WO/2021/154727A1 |
An air-breathing rocket engine in certain embodiments comprises an hourglass-shaped outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake that ...
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WO/2021/151951A1 |
An outlet guide vane (OGV) structure for a gas turbine engine comprises a plurality of radially extending guide vanes (30), at least one guide vane comprises at least one inlet (35) allowing air to pass into at least one internal cavity ...
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WO/2021/146779A1 |
Pulse detonation propulsor Vujin, is a high stage in the development of pulse detonation propulsors. It is intended primarily for the propulsion of aircraft, and with minor modifications it can also be used as a combustion chamber for th...
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WO/2021/151036A1 |
A sound attenuating engine exhaust system and methods are provided for directing exhaust gases away from an internal combustion engine of a vehicle and attenuating undesirable exhaust sounds during engine operation. The sound attenuating...
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WO/2021/148743A1 |
Fan module (20) for an aircraft turbomachine testbed, this module comprising: - a drive shaft (22), - a fan (24) comprising a disc (26) and bearing blades (28) extending substantially radially outward from the disc, and - a thrust balanc...
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WO/2021/144519A1 |
The invention relates to an assembly (1) for a turbine engine extending along an axis, comprising a stator, a low-pressure compressor shaft (4), a low-pressure compressor comprising a rotor comprising a drum (2) rotatably coupled to the ...
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WO/2021/142120A1 |
An insulation precursor composition comprises ethylene propylene diene monomer, an aramid, and a bromine-containing flame retardant. Rocket motors comprising a case, an energetic material within the case, and an insulation material compr...
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WO/2021/140053A1 |
The invention relates to a rocket engine nozzle (1) with a variable cross-section, the nozzle comprising: - a stationary part (2); and - a movable part (3), capable of moving between a retracted position, in which the movable part (3) su...
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WO/2021/136898A1 |
The invention relates to a thrust reverser (40) for an aircraft propulsion assembly, this reverser (40) comprising a lower door (46) and an upper door (47) defining, in thrust reversal configuration, a deflection opening, through which a...
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WO/2021/138538A1 |
A method of reducing noise from a high-speed, including supersonic, jet, the method includes providing the high-speed or supersonic jet in a longitudinal flow direction; and inducing a rotation of a swirl layer of the high-speed or super...
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WO/2021/136903A1 |
The invention relates to a thrust reverser (40) comprising a stationary structure (41), a lower door (46) and an upper door (47). This reverser (40) comprises at least one deflector (60) configured to be able to redirect forward (42) fro...
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WO/2021/136911A1 |
A system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the th...
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WO/2021/136902A1 |
The invention relates to a thrust reverser (40) comprising doors (46, 47) and at least one flexible deflector (60A-60D) that closes a lateral opening in the reverser (40) when the doors (46, 47) are open. Such a deflector (60A-60D) makes...
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WO/2021/136899A1 |
The invention relates to a thrust reverser (40) for an aircraft propulsion assembly, this reverser (40) comprising a lower door (46) and an upper door (47) defining, in thrust reversal configuration, an asymmetric deflection opening, thr...
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WO/2021/136900A1 |
The invention relates to a thrust reverser (40) comprising a stationary structure (41), a lower door (46) and an upper door (47). Said reverser (40) comprises at least one deflector (60) configured to be able to redirect, to the rear (43...
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WO/2021/123621A1 |
The present application relates to a thrust reverser (1) for a turbojet aircraft nacelle, comprising: - a fixed structure (10), - a mobile structure (11), - an actuator (2) extending along a main axis (A1) and connected by a first connec...
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WO/2021/123628A1 |
The invention relates to a tool and a method for manufacturing an openwork element made of composite material, the tool comprising - a first (12) and a second flange, each flange being configured to be arranged on either side of the open...
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WO/2021/124205A1 |
The present invention is mainly based on Base Integrated Symmetrically or Asymmetrically Rationed (Especially Golden Aspect Rationed) Double Cones (BISARDC), supported by cantilever support (4), and are implemented in between blades (8)/...
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WO/2021/121976A1 |
The invention relates to a gas turbine engine (1) of an aircraft, comprising an inner engine region (27) and an outer engine region (28), which delimit a flow cross-section (2) and are operatively interconnected by means of braces (22, 2...
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WO/2021/123639A1 |
The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (3...
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WO/2021/116600A1 |
Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first t...
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WO/2021/116621A1 |
The present invention relates to an aero-propulsion system (1) comprising: - a drive shaft (10), - a low-pressure compressor (4), - a fan shaft (13) driving a fan (2), - a reduction mechanism (12) coupling the drive shaft (10) and the fa...
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WO/2021/116591A1 |
The invention relates to a heat exchanger (16) between a fluid and an air flow (FS), comprising a heat exchange wall (17) separating the fluid and the air flow (FS), the heat exchange wall (17) having a heat exchange surface (18) which e...
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WO/2021/116556A1 |
Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bear...
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WO/2021/118530A1 |
A nozzle assembly according to an exemplary aspect of the present disclosure includes, among other things, a nozzle including a throat section. The nozzle further includes a ball portion of a ball and socket joint. The assembly further i...
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WO/2021/118536A1 |
A liquid fuel rocket engine according to one example includes a combustor, a liquid fuel repository connected to the combustor via a fuel line and a first valve, an oxidizer repository connected to the combustor via an oxidizer line and ...
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WO/2021/116620A1 |
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13) comprising two reduction stages (27, 32) and including: - a sun gear (33), ...
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WO/2021/116592A1 |
The invention relates to an assembly for a turbomachine through which an air flow flows, comprising a stator (6) having guide vanes (7) that extend radially relative to a longitudinal axis (AX), at least one inter-vane platform (19) that...
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WO/2021/116557A1 |
Aircraft turbine engine (10), comprising: - at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V), - an annular exhaust casing (28) supporting at least one bear...
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