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WO/2022/055673A1 |
Mining apparatuses, systems, and methods related to using a rocket engine's plume and a collection manifold to efficiently displace, collect, process, and store frozen volatiles embedded within or below a surface are disclosed. The plume...
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WO/2022/051849A1 |
A turboramjet has a housing with an intake and an exhaust. The housing houses a heat exchanger, a turbojet section and a ramjet section downstream of the turbojet section. The heat exchanger has an air path and a coolant path. The air pa...
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WO/2022/053496A1 |
In order to improve a thrust chamber device, comprising a thrust chamber with a thrust space which has a first section, a second section which adjoins the latter, and a third section which adjoins the second section, wherein the thrust s...
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WO/2022/056107A1 |
An integrated fuel cell power delivery system includes a first power source configured to supply power to a propulsion inverter, a second power source configured to supply power to the propulsion inverter, a disconnect operably connected...
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WO/2022/054678A1 |
A rocket engine 100 comprises a combustion chamber 110 and a rocket nozzle 140 that communicates with the combustion chamber 110. A metal wire supply device 120 supplies a metal wire 2, which is fuel, to the combustion chamber 110. A ste...
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WO/2022/055545A1 |
A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes...
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WO/2022/049342A1 |
The invention relates to an assembly (50) for an aircraft turbine engine, comprising a fan (15), a speed reduction gear (20) and an intermediate casing (25) comprising an internal annular structure (52) that houses an epicyclic gear trai...
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WO/2022/045435A1 |
Disclosed is a hygroscopic flare ejection-type rocket for artificial rainfall, comprising: a rocket body that is dropped by means of a parachute after flying by thrust and has an outlet for discharging hygroscopic flares; a communication...
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WO/2022/043327A1 |
A hot-gas-generating apparatus for reacting a propellant comprises a combustion chamber, at least one injector that is arranged upstream of the combustion chamber and can be closed, on the combustion chamber side, to the propellant, elec...
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WO/2022/043293A1 |
The invention concerns a jet-engine comprising an outer casing having an opening end for allowing inlet gas to enter therein, a combustor system comprising a combustor container enclosing a combustor chamber, a hot gas combustor inlet fo...
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WO/2022/034083A1 |
Method and system for controlling the thrust of an aircraft turbomachine (100) having a high bypass ratio by direct action on a variable-pitch system (123) for varying the pitch of the vanes of a stator (121) of a low-pressure compressor...
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WO/2022/018368A1 |
Fuel pump (1) for an aircraft engine, comprising an inductor (10) and an impeller (20) which are attached to each other and have an axis of rotation (X), an annular space (E) axially spacing the inductor (10) and the impeller (20), and t...
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WO/2022/018345A1 |
The invention relates to a thrust reverser for a propulsion unit, comprising movable grids, two half-assemblies forming part of a secondary stream and, at the six o'clock position, a connecting beam (60) intended to be mounted in cantile...
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WO/2022/011407A1 |
The invention relates to a cascade element (1) for a thrust reverser system (22) of an engine (20), more particularly a jet engine, comprising a number of mutually adjacent deflecting vanes (2) for deflecting an air flow, at least one of...
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WO/2022/013459A1 |
A jet engine for propelling aircraft, capable of providing thrust from rest to high speeds. Characterised in that it employs a liquid oxidant and two liquid fuels of different molecular weights. The engine has an axial compressor (16) or...
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WO/2022/006304A1 |
The subject matter of this specification can be embodied in, among other things, a thrust reverser synchronization shaft lock system includes a rotatable shaft comprising at least one radial prong extending radially from the shaft, a hyd...
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WO/2021/260531A1 |
A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. T...
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WO/2021/260285A1 |
The invention relates to a thrust reverser for an aircraft propulsion unit. The thrust reverser comprises three gates (31,32, 33) that can be deployed downstream of an outlet section of the propulsion unit. The invention increases the po...
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WO/2021/262225A1 |
A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end...
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WO/2021/262226A1 |
A rocket engine nozzle manufacturable and applicable to tactical missile designs includes an aerospike having a plurality of airfoil fins distributed radially around a central longitudinal axis of a rocket engine blast tube.combustion ch...
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WO/2021/263163A1 |
An autothrottle of an aircraft is configured to reduce engine power of the aircraft such that the aircraft incrementally slows from a prior airspeed to a reduced airspeed by a first increment, and compare the rates of energy consumption ...
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WO/2021/257045A1 |
The invention relates to aviation technology and is intended for use as a power plant in both supersonic and subsonic passenger aircraft. Owing to the design of the claimed pure turbojet engine, when an aircraft is flying at supersonic s...
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WO/2021/249184A1 |
A two-duct turbojet engine, comprising ducts, an air inlet mechanism (1) arranged at an air inlet end of the ducts and an exhaust nozzle (5) arranged at an air outlet end of the ducts, wherein the ducts comprise an outer duct (3) and an ...
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WO/2021/249186A1 |
A high-efficiency, three-duct power propeller with a high thrust-weight ratio, the power propeller comprising ducts and an intake mechanism (1) arranged at the intake end of the ducts, wherein the ducts include an inner duct (2), a middl...
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WO/2021/249185A1 |
A large thrust-to-weight ratio efficient propeller having a secondary expansion working capability, comprising an air inlet mechanism (1), ducts (2, 3) and a flow-increasing mechanism (4); the air inlet mechanism is provided at an air in...
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WO/2021/250336A1 |
Disclosed is a counterrotating turbine (C) for a turbomachine (10), extending around an axis of rotation (X) and comprising an inner rotor (22) having at least one movable inner blade (220) rotationally supported by a first shaft (26), a...
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WO/2021/250584A2 |
The thrust reverser system (60) for an aircraft turbofan propulsion system (30) comprises: a fixed structure (80) and a translating structure (90) adapted to define between them a sequential flow path for air, the translating structure (...
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WO/2021/250339A1 |
A turbomachine of longitudinal axis (X-X') comprising a fan that delivers a main airflow (F) and a separating member (20) that is configured to separate said airflow (F) into a primary airflow (F1) flowing in an inner duct (VI) and a sec...
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WO/2021/246906A1 |
A cowling of a turbojet engine gas generator comprises a shell consisting of an upstream portion and a downstream portion. The upstream portion is provided with at least one pair of hinges in the upper part of the gas generator nacelle. ...
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WO/2021/246247A1 |
A method of reprocessing a metal product according to the present invention including: a welding process for welding a dummy member to the metal product; a reprocessing process for reprocessing the metal product in a state in which the m...
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WO/2021/245821A1 |
In this propulsion system mounted in a spacecraft, it is necessary to raise the temperature of a reactor in order to improve performance. However, since a catalyst for causing the continuous self-decomposition of a high-energy substance ...
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WO/2021/246905A1 |
A system comprises an electronic engine regulator having two electronic control channels configured to allow the exchange of information between said channels and to allow each channel to issue control commands to open or close a thrust ...
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WO/2021/234245A1 |
The invention relates to a piece comprising a first metal part (12) and a second part (14) made of an organic matrix composite material, in which the first part (12) has a first connecting portion (12A) and the second part (14) has a sec...
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WO/2021/234244A1 |
The invention relates to a piece comprising a first metal part (12) and a second part (14) made of an organic matrix composite material, in which the first part (12) has a first connecting portion (12A) and the second part (14) has a sec...
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WO/2021/234279A1 |
The invention relates to a nacelle for a propulsion assembly, said nacelle comprising a front internal structure (14) having a framework formed of longitudinal beams (20) and comprising removable, dismountable or retractable panels (21) ...
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WO/2021/234242A1 |
The invention relates to a method for assembling a first metal part (12) with a second part (14) made of an organic matrix composite material, the first part (12) having a first connecting portion (12A) and the second part (14) having a ...
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WO/2021/234254A1 |
Thrust reverser (30) for an aircraft bypass turbojet engine nacelle, said thrust reverser having a generally annular shape around an axis and comprising an annular frame (34) for securing deflection grids (38), said frame (34) comprising...
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WO/2021/226681A1 |
Claimed is a device for passively reversing flows of pressurized fluid and capturing the momentum thereof. The device, in the form of a nozzle, is mounted at the outlet of an external power device that generates reactive thrust, such as ...
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WO/2021/229163A1 |
The invention relates to an exhaust case (15) for a turbomachine extending along a longitudinal axis (X), comprising: an annular shroud (23) having a wall (24) extending along the longitudinal axis (X) from a first flange (25), a plurali...
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WO/2021/230983A1 |
A rocket motor (22) for a gun-fired projectile (20) is configured to stiffen the burnable propellant in the rocket motor during burning and/or protect the rocket motor from the pressure that occurs during firing of the projectile from th...
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WO/2021/225621A1 |
A thrust generator is provided for producing thrust to move a spacecraft. The thrust generator includes a housing having a first end and an opposing second end. The first end is associated with a mount for coupling to the spacecraft. The...
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WO/2021/223028A1 |
The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system...
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WO/2021/214402A1 |
The invention relates to a turbine engine (1) wherein an inlet flow (F) is separated into a first stream (Fp) flowing through a first vein (16) and a second stream (Fs) flowing through a second vein (17), and comprising a gas generator (...
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WO/2021/205107A1 |
A discharge grid (22) designed to be mounted inside or at the outlet of a line (21) of a discharge valve (20) of a turbomachine (1) of an aircraft, the discharge grid (22) comprising an upstream face (24) designed to receive a gas flow (...
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WO/2021/205120A1 |
An acoustic treatment grid (22) designed to be mounted inside or at the outlet of a line (21) of a discharge valve (20) of a turbomachine (1) of an aircraft, this being designed to convey a gaseous flow (F), the grid (22) comprising a pe...
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WO/2021/198581A1 |
The invention relates to a dual flow aircraft propulsion assembly (1) comprising a retractable heat exchanger (25). The exchanger (25) can be deployed in a secondary channel (11B) of the propulsion assembly (1) so as to cool a fluid flow...
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WO/2021/198570A1 |
A thruster assembly, comprising a switch (1) connected to a power source, a thruster (2), a propellant tank (3) for storing and pressurising a propellant, and a propellant channel (5) for guiding the propellant to the thruster (2). The t...
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WO/2021/198617A1 |
The invention relates to a thrust reverser (20) for a turbojet engine mounted on an engine pylon (40), comprising a fixed part (29) and a movable part (39), that is coaxial and mounted movable in translation relative to the fixed part (2...
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WO/2021/199802A1 |
A static blade (30) provided in the rear of a rotor blade (21) comprises a blade main body (32) having a blade-shaped cross-section (31). The maximum blade thickness position (M) of the blade main body (32) in the blade-shaped cross-sect...
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WO/2021/191569A2 |
Turbomachine (10) for an aircraft, comprising a casing (30), a fan (20), a compressor (50) and a turbine (90), and a planetary gearing (40) comprising an input that is driven in rotation by the turbine (90), a first output stage configur...
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