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WO/2024/094947A1 |
The invention relates to a thrust reverser (100) comprising: - a stationary structure (20) and a movable structure (21) mounted opposite an opening (22); - an actuator (30-33) for selectively moving the movable structure (21) between a d...
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WO/2024/093078A1 |
The present application relates to the technical field of injectors. Disclosed is a variable thrust pintle type injector, which aims to solve the problems of a complex structure and low operating reliability of an injector due to strict ...
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WO/2024/096879A1 |
A gas turbine engine including a turbomachine. The turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine including an inlet duct defining an engine inlet,...
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WO/2024/089909A1 |
A propellant supply system (100) for supplying fuel (F) and an oxidizing agent (O) to an object (R) to be supplied with a propellant comprises: an axial gap motor (10) having a rotating shaft; a fuel pump (30) provided at one end of the ...
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WO/2024/088516A1 |
Air turborocket apparatus (10) including an air intake (11), a compressor (12), a turbine (13), a gas generator system, a coupling system (19), a combustion chamber (14), and a nozzle (15). The air intake is designed to receive atmospher...
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WO/2024/084160A1 |
The invention relates to a turbojet engine comprising: a combustion chamber and a jet pipe; a main circuit (11) including a main centrifugal pump (14) and a main positive displacement pump (16) supplying fuel to the injectors (18) of the...
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WO/2024/079461A1 |
There is disclosed a rocket engine arranged to deliver one or more propellants to a combustion chamber of the rocket engine for generating motive thrust. The rocket engine comprises an electrical transmission system, a turbine generator ...
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WO/2024/080873A1 |
In an aspect of the invention there is provided a solid fuel propelled projectile, comprising: an elongated projectile motor case and/or a core piece having solid fuel provided thereon to form a combustion chamber between the motor case ...
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WO/2024/081852A1 |
Some embodiments of the present disclosure are directed to a rocket engine, comprising a primary chamber and a double contour nozzle attached to the primary chamber. In some embodiments, the double contour nozzle comprises an inner conto...
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WO/2024/074743A1 |
The invention relates to a microthruster applicable to space engineering that comprises printed circuit boards (PCBs) connected to each other, wherein the first board comprises a fuel tank (1) and an outlet nozzle (2) and the second boar...
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WO/2024/074993A1 |
A thruster (100) for orbital maneuvers comprises a divergent channel (111) having an axial axis of symmetry (S); a combustion chamber (110); a throat (112) interposed between the combustion chamber (110) and the divergent channel (111); ...
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WO/2024/069110A1 |
The invention relates to a thrust reverser (30) comprising a stationary structure (31) and a movable structure (29) comprising at least one movable reverser cowl (33) having a cavity (54) delimited between a radially outer wall (50) and ...
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WO/2024/069111A1 |
The invention relates to a thrust reverser for an aircraft propulsion assembly, the reverser comprising a stationary structure (31) equipped with a radially inner wall (18) delimiting a secondary flow path (21B), the reverser also compri...
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WO/2024/069083A1 |
One aspect of the invention relates to a nozzle (1) comprising: - a spray gas supply pipe (2); - a mixing chamber (3) for mixing spray gas and powdered material into an accelerated mixture which is connected, via an upstream end (31), to...
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WO/2024/069109A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, comprising a stationary structure (31) equipped with a radially inner wall (18) delimiting a secondary flow path (21B) through which a secondary flow (2...
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WO/2024/068395A1 |
The invention relates to a rocket engine (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), wherein the first tank is filled with a fuel and the second tank with an oxidising agent, such as liquid hydrogen peroxi...
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WO/2024/063751A1 |
A gasification chamber of a rocket engine for a solid propellant charge, the charge consists of a shell that is made of a solid polymeric propellant and a solid oxidizer that is arranged within a volume. An inner surface of the chamber i...
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WO/2024/061558A1 |
A gas turbine engine has a core flow path and an outer flow path, the outer flow path positioned at a greater radial displacement from a rotational axis of the engine than the core flow path. The gas turbine engine also has a cavity to p...
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WO/2024/062174A1 |
The invention relates to a thrust reverser comprising a sealing membrane (58) designed to deflect at least one portion of a secondary flow towards a deflection cascade (32) when a movable structure of the reverser is in the retracted rev...
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WO/2024/063684A1 |
An igniter (100), for igniting explosives or pyrotechnic composition, comprising a container (102) for housing explosives or pyrotechnic composition (102a); and an electronic circuitry (104) comprising, two conducting electrodes (106), e...
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WO/2024/064270A1 |
An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that ...
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WO/2024/061737A1 |
The invention relates to a turbomachine comprising: a first splitting edge capable of separating an incoming air flow into a radially internal air flow and a secondary air flow; a second splitting edge capable of separating the radially ...
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WO/2024/051938A1 |
An air turborocket engine (10), comprises a fuel tank (14), in particular comprising hydrogen, a main combustion chamber (19), a turbine (18), a compressor (21), and a first inlet opening (23) for feeding air into the main combustion cha...
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WO/2024/052725A1 |
A method and disc that gasifies and pressurizes liquid propellants for use in rocket propulsion systems. The method involves the following steps: a) Increasing the tangential kinetic energy and pressure of liquid propellants by driving t...
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WO/2024/047320A1 |
The present invention relates to a jet propulsion system provided with a hybrid rocket engine and, more specifically, to the storage of the fuels before they are introduced into the combustion chamber. This propulsion system is made up o...
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WO/2024/050004A1 |
A cold gas thruster having a two-stage solenoid is provided. Pressurized gas from the inlet flows to the back side of the piston (134) to hold the piston closed. The pressure is maintained by a check ball held by the solenoid armature. W...
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WO/2024/038232A1 |
The present invention relates to a turbomachine assembly (1), comprising: - a high-pressure compressor (5) configured to be driven by a high-pressure shaft (12); - a low-pressure compressor (4) configured to be driven by a low-pressure s...
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WO/2024/038016A1 |
Order fulfillment system with a floor-based order fulfilment area in which at least one picking station is arranged, wherein the picking station includes source item providing means and order collection providing means, such that orders ...
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WO/2024/028551A1 |
The invention relates to an exhaust system (18) for a turbine engine, comprising a nozzle (20) at least partly delimiting a gas exhaust path. The system comprises a heat exchanger (26) comprising at least one distributor (28), at least o...
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WO/2024/023422A1 |
The present invention relates to a method for controlling an electrical system, comprising: processing a main command signal (IP) for commanding drawing of a mechanical power by the electrical system from an electrically hybridized turbo...
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WO/2024/023439A1 |
The invention relates to an electrical power generation and distribution system 1 for a hybrid-electric propulsion aircraft powered by at least one turbojet engine (10). The system comprises at least N ≧ 2 (N integer) distribution netw...
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WO/2024/021318A1 |
A method and device for an aviation aircraft to use relative motion air kinetic energy, which, by means of a relative motion air kinetic energy recoil thrust generating device (9) provided on an aviation aircraft, highly amplify relative...
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WO/2024/023432A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion unit, the reverser comprising a movable structure (29) translatably movable relative to a fixed structure (18) between an advanced direct thrust position and a re...
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WO/2024/019721A1 |
The invention includes engines adapted for using apparatuses and methods for instantiating chemical reactants in a nanoporous carbon powder, and further includes uses for such engines and vehicles incorporating such engines. The inventio...
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WO/2024/017865A1 |
Aerospike engine portion, comprising: - a tube like housing including an outer wall, - a preferably substantially conical spike part arranged at the lower side of the housing in the exhaust of the engine part - fluid lines extending from...
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WO/2024/013462A1 |
The present invention relates to a method and system for managing the drawing of mechanical power from a two-spool or three-spool turbine engine (1) for an aircraft, in which at least two electric machines (3, 4) are suitable for recover...
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WO/2024/013444A1 |
The present invention relates to a turbine engine turbine assembly (10) having a longitudinal axis (X), the assembly comprising an exhaust cone (40) having an upstream portion (40a) and a downstream portion (40b), the upstream portion (4...
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WO/2024/009024A1 |
The invention relates to a propulsion unit comprising: an electric motor (10), which includes an annular stator (11) about a longitudinal axis (X) and a rotor arranged radially inside the stator (11), so as to be rotated about the longit...
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WO/2024/009021A1 |
The invention relates to a method for controlling a hybrid turbine engine (11) for an aircraft, the turbine engine (11) comprising a low-pressure shaft (10), a high-pressure shaft (9), at least one power conversion device (13) mounted on...
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WO/2024/009020A1 |
Disclosed is a twin-spool turbomachine comprising a low-pressure turbine (5) connected to a low-pressure compressor (1) by a low-pressure rotation shaft (10) and a high-pressure turbine (4) connected to a high-pressure compressor (2) by ...
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WO/2024/008781A1 |
The invention relates to an injector for a rocket engine, comprising a main part (10, 12) in which a fuel feed and an oxidator feed are provided and comprising an adjusting element (20) which, in cooperation with the main part (10, 12), ...
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WO/2024/006185A1 |
A redundant fuel metering system and method for a multi-stage combustor that utilizes a fuel metering valve EHSV from a less critical combustor stage fuel metering system as a redundant backup to the main metering valve EHSV. In the even...
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WO/2024/003083A1 |
The invention concerns an aircraft fuel heating arrangement comprising an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more cond...
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WO/2024/003756A1 |
For example, a controller of an Active Acoustic Control (AAC) system may be configured to process input information including AAC configuration information, and a plurality of noise inputs representing acoustic noise at a plurality of no...
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WO/2024/002034A1 |
A fixing device for temperature sensors in a combustion chamber of a solid rocket engine, comprising anti-static materials (1) and an elastic supporting part. The two anti-static materials (1) are fixedly installed at two ends of the ela...
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WO/2024/006730A1 |
Dynamic ram accelerator operation permits operation with lower acceleration, permitting launch of acceleration sensitive payloads such as crewed vehicles. Operational cost is reduced, and reliability improved, by reducing or eliminating ...
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WO/2023/247893A1 |
The invention relates to a blocker door for a thrust reverser, preferably having screens and a sliding cover, the blocker door comprising: a structural frame (14) which is configured to ensure the mechanical strength of the blocker door;...
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WO/2023/249660A1 |
An integrated hydrogen-electric engine includes, an air compressor system; a hydrogen fuel source; a fuel cell; an elongated shaft connected to the air compressor system or a propulsor; and a motor assembly disposed in electrical communi...
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WO/2022/173709A9 |
An expendable launch vehicle is provided using pressure-fed liquid propellant fixed steering ablatively-cooled rocket engines. The vehicle is manufactured minimizing toxic or exotic metals and maximizing the use of conventional, inexpens...
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WO/2023/246980A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine ...
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