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WO/2022/219270A1 |
The invention relates to a movable-cascade thrust reverser comprising a multifunctional annular fixed structure (31) configured to be rigidly connected to a fan casing of a turbine engine or to an intermediate casing secured to the fan c...
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WO/2022/220776A1 |
The present invention relates particularly to an ablative thermal insulation material with increased erosion performance comprising EPDM rubber material containing organic reinforcement increasing erosion resistance, inorganic reinforcem...
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WO/2022/219274A1 |
The invention relates to an acoustic panel (12) for a turbine engine, comprising a first strip (20) and a second strip (22) each comprising an alternation of first (20a, 22a) and second (20b, 22b) ridges which are connected by flanks (20...
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WO/2022/219082A1 |
The invention relates to a power plant unit (1) for a rocket drive, with a combustion chamber (2) which extends along a centre longitudinal axis and has a surrounding wall (24), an injector unit (3) which is mounted at the input side of ...
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WO/2022/216932A1 |
Lobed mixer nozzles for supersonic and subsonic aircraft, and associated systems and methods are disclosed herein. A representative lobe mixer nozzle includes a fan flow duct aligned along a longitudinal axis, and a core flow duct, also ...
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WO/2022/216468A1 |
Lobed mixer nozzles for supersonic and subsonic aircraft, and associated systems and methods are disclosed herein. A representative lobe mixer nozzle includes a fan flow duct aligned along a longitudinal axis, and a core flow duct, also ...
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WO/2022/208801A1 |
This fan case assembly for a turbofan engine comprises: a cylindrical fan case that surrounds a fan of the turbofan engine from the outside in the radial direction; a cylindrical panel set that covers the inner circumferential surface of...
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WO/2022/212759A1 |
A hybrid hydrogen-electric and hydrogen turbine engine and system is disclosed. The hydrogen-electric system has an air inlet, a hydrogen fuel source, a fuel cell stack, and a motor assembly disposed in electrical communication with the ...
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WO/2022/212321A1 |
Leveraging a turboexpander to provide additional functionality in compressed gas fueled systems is disclosed. The system includes a compressed gas storage device storing a compressed gas at a first pressure. A turboexpander operably coup...
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WO/2022/208048A1 |
A pumping apparatus comprising: a pump having a plurality of chambers for sequentially supplying fuel to a combustion chamber; wherein each chamber is fluidly connected to another chamber such that venting of the chamber at least partial...
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WO/2022/200728A1 |
Thrust reverser (30) comprising a jack (40) for translational actuation of a movable part (32, 33), the jack (40) being a screw jack (41) without an extension tube.
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WO/2022/197211A1 |
Rotary systems are driven by jet engines disposed on the end of a rotor comprising a structure that rotates about a rotary shaft. A jet stream produced by a jet engine generates thrust orthogonal to the radius of the rotor, thereby stimu...
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WO/2022/189157A1 |
Disclosed is a fuel conditioning system (SC) configured to power an aircraft turbine engine (T) using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one first heat exchanger (31) configured to heat ...
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WO/2022/191878A1 |
A dual mode ramjet or scramjet engine (10) used in the propulsion of an aircraft includes an inlet (14) configured to receive and compress air, a combustion chamber (16) connected to the inlet and configured to mix the compressed air wit...
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WO/2022/185165A1 |
A propulsor system comprising a propulsor and an exhaust area control mechanism are described. The exhaust area control mechanism is connected to an outlet of the propulsor and is configured to vary the area through which air exits the p...
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WO/2022/185164A1 |
A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blade fan is tensioned at the tips of the plurality of blades. By tensioning the tips o...
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WO/2022/184355A1 |
The present invention provides an engine (310) of a vertical take-off and landing aircraft (300), wherein the engine is configured to be movable with respect to an aircraft component (342) of the aircraft (300) between a hover position f...
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WO/2022/185163A1 |
A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blad...
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WO/2022/184530A1 |
An air inlet (1) of a nacelle (2) of an aircraft propulsion assembly (8) comprising an inner wall (11) and an outer wall (12) which are connected upstream by an air inlet lip (13), the air inlet lip (13) comprising thick portions and thi...
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WO/2022/184499A1 |
The present invention provides an engine (310) of a vertical take-off and landing aircraft (300), wherein the engine is configured to be movable with respect to an aircraft component (342) of the aircraft (300) between a hover position f...
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WO/2022/180382A1 |
A rocket propulsion system (200, 300, 400, 500, 600) comprising: a propellant tank (208, 306, 308, 406, 408, 506, 508, 606, 608) arranged to contain propellant, a liquid pressurant tank (202, 302, 402, 502a, 602a) arranged to contain a l...
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WO/2022/177593A1 |
A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The casing may itself at least in part define an annular gap that functions as a nozzle for the r...
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WO/2022/177594A1 |
A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The rocket booster also includes one or more nozzle pieces, mechanically coupled to the casing, t...
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WO/2022/175739A1 |
Ramjet or Scrum jet aircraft engine with the capability of mounting two fans behind the aircraft's nozzle. This invention installed in the exhaust section of the aircraft (behind the aircraft nozzle). It has two fans, one of which is loc...
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WO/2022/178115A1 |
A system can include an emitter structure connected to a reservoir containing a working material, wherein the working material is in electrical communication with a first electrode, an electrode opposing the emitter structure across a ga...
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WO/2022/175620A1 |
A rear portion of a convergent-divergent nozzle turbojet engine comprises means for controlling the position of a divergent flap relative to that of a convergent flap, comprising a first connecting rod (120) having a first end portion (1...
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WO/2022/171727A1 |
The invention relates to a propulsion system (1) for an aircraft, which propulsion system comprises a rotor (2; 2b; 2c) having a rotor main body (4-4c) and rotor blades (3; 3b; 3c) attached to the rotor main body (4-4c), wherein air can ...
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WO/2022/167754A1 |
The invention relates to a thrust reverser with movable grids, comprising means for connecting, by recessing, a front frame (52) of an outer cowl and a rear frame (53) of the grids. The reverser comprises loading means configured to exer...
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WO/2022/156925A1 |
The invention is about a combustion section (01) of a gas turbine (02) comprising an annular combustion chamber (07), and a burner arrangement (08) upstream of the combustion chamber (07), and an annular compressor diffusor (15), and an ...
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WO/2022/158788A1 |
A jet-propelled engine using discharged exhaust gas is disclosed. A jet-propelled engine using discharged exhaust gas, according to an embodiment of the present invention, comprises: a body; a combustor installed in the body so as to spr...
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WO/2022/152994A1 |
The invention relates to a propulsion assembly (200) for an aircraft comprising a double-flow turbomachine (1) equipped with a fan (15), an aerodynamic outer casing (5) forming a nacelle, and a mounting pylon, the propulsion assembly hav...
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WO/2022/152688A1 |
An aerospike engine configured to be connected to a liquid methane tank, and to a liquid oxygen tank is provided. The aerospike engine comprises a centerbody including an aerospike nozzle, an external skirt, and a combustion chamber bein...
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WO/2022/148942A1 |
A jet vectoring apparatus has a nozzle (1) which comprises a throat aperture (8) and an exit aperture (9), the apparatus also having a post exit surface (10). Variation of at least one of the throat aperture (8), exit aperture (9) and po...
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WO/2022/148928A1 |
Stator assembly for straightening an air flow, turbojet engine, turbofan engine and aircraft, the assembly comprising a plurality of stator vanes distributed around an axis of revolution of the stator assembly, wherein for each stator va...
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WO/2022/150492A1 |
A method of generating a momentum change in a vehicle by phase changing matter in a closed system is used to change the momentum of the vehicle without the need of a combustion system for propulsion. The method uses the multi-phase dynam...
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WO/2022/144748A2 |
The present invention describes a system for storing or producing electricity, which allows the stabilization of the power network under conditions of excess availability of electricity or lack thereof and for the possible production of ...
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WO/2022/146290A1 |
This invention relates to at least one engine (2) of the type used in air vehicles; exhaust gas generated by the operation of and removed from the engine (2); at least one nozzle (4) with an almost entirely cylindrical geometry, position...
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WO/2022/136324A1 |
A plasma-facing component for a plasma chamber, comprising: a plasma-facing target surface; an inlet through which to receive a coolant fluid and an outlet through which to expel the coolant fluid; and a plurality of internal cooling cha...
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WO/2022/139054A1 |
According to one aspect of the present invention, provided is a device for opening an intake port of a ramjet engine, the device comprising: a duct part having an intake port; a shutter part for covering the intake port when the intake p...
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WO/2022/133514A1 |
An aspirator for a propulsion system providing a thrust output enables improved efficiency. The aspirator comprises a shroud configured to at least substantially enclose a thrust output end of the propulsion system, the shroud comprising...
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WO/2022/140040A2 |
Methods and apparatuses for reducing engine noise provided. In one embodiment, an apparatus is provided that includes a plurality of seals and flaps that are interconnected and circumferentially arranged. Also included are a plurality of...
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WO/2022/131959A1 |
The invention relates to jet engines, and more particularly to pulse detonation engines. The desired technical result, namely increased energy efficiency and reliability, is achieved in an engine having a combustion chamber configured in...
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WO/2022/129778A1 |
Disclosed is an acoustic treatment panel comprising acoustic absorption cells (18) each comprising a bottom wall (180), a porous inlet wall (181), an enclosure (185) extending in an axial direction (DA) between the bottom wall (180) and ...
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WO/2022/127251A1 |
A solid attitude and orbit control engine gas valve. The solid attitude and orbit control engine gas valve is fixedly connected below a combustion chamber of a solid rocket engine of an aircraft; the gas valve comprises a valve body (1),...
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WO/2022/122367A1 |
An electric motor (1) comprises a stator (10) defining an inner space (100); a rotor (11) arranged in the inner space (100) of the stator (10); and a bearing arrangement (12) rotatably supporting the rotor (11) on the stator (10) and com...
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WO/2022/123142A1 |
A turbomachine assembly having a longitudinal axis and comprising a turbine exhaust casing (30); an exhaust cone (40) arranged downstream of the exhaust casing (30) and comprising an upstream portion (40a) and a downstream portion (40b),...
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WO/2022/123163A1 |
Said device (16) for controlling an electrical thrust reverser control system (1) for an aircraft comprises electrical supply means (9) and control means (19) which are configured to couple the electrical supply means (9) to the electric...
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WO/2022/117968A1 |
A multicellular acoustic-attenuation panel (220) comprises several rows of acoustic cells (240, 250, 260, 270, 280) each extending in a circumferential direction (DC), each acoustic cell being delimited by a wall (241, 251, 261, 271, 281...
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WO/2022/116652A1 |
The present invention relates to a method for predicting a structural response of a liquid-propellant rocket engine to an impact load. The purpose of the present invention is to solve the technical problem in the prior art of it being di...
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WO/2022/117938A1 |
The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a t...
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