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WO/2020/152418A1 |
The invention relates to a noise reducing device (18) for an aircraft turbine engine, said device having a structure in the form of a stack of layers (20, 22, 24), such that a first and a second skin (22, 24) made of composite material f...
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WO/2020/147860A1 |
A method for forming a nozzle component of an aerospace engine comprises the following steps: step 1, cutting a sheet (1) to obtain a plurality of coaxial truncated hollow cones (3); step 2, performing spinning and straightening on the t...
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WO/2020/148493A1 |
The invention relates to an aerodynamic arm (100) for an aircraft turbine engine casing, characterised in that it comprises: - a tubular outer shell (110) having a generally elongate shape extending substantially along an axis (A-A), the...
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WO/2020/146928A1 |
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/2020/143097A1 |
A system for treating fuel jet plume exhausted from a motor is used to treat fuel jet plume exhausted from a motor. The motor comprises an injector (94) for expansion and acceleration of a fuel gas. The system for treating fuel jet plume...
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WO/2020/142335A1 |
Technologies for providing noise shielding are described herein. In some examples, noise shields are installed proximate to one or more of the main engines of the aircraft. The noise shields can be extended during terminal operations and...
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WO/2020/136684A1 |
This patent discloses system for generating additional thrust from the turbine of an exoskeletal turbofan jet engine. System consists of externally located rim driven ducted propeller coupled to the inner rotary drum of the exoskeletal t...
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WO/2020/134005A1 |
Provided is a throat offset pneumatic vector nozzle having an asymmetric rear body profile, comprising a nozzle body, the rear body profile of the nozzle body being arranged as an asymmetric structure. Under normal circumstances, upper a...
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WO/2020/126848A1 |
The invention relates in particular to a power plant assembly, comprising - a turbine (TT) for driving at least one rotor shaft (RS); - a combustion chamber (76) for generating drive energy for the turbine (TT); - at least one electric m...
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WO/2020/123601A1 |
A combustion chamber liner comprising a plurality of spiral cooling channels is formed from a material component. A combustion chamber liner body extends from a first end and a second end. The combustion chamber liner body comprises a co...
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WO/2020/120249A1 |
Power device based on alkali-water reaction, having a reaction chamber (1) to carry out a chemical reaction between water and alkali element, comprising an exhaust nozzle (13) to exhaust the reaction products generated in the reaction ch...
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WO/2020/115382A1 |
The invention relates to an engine assembly (200) for an aircraft comprising a bypass turbomachine as well as a turbomachine attachment pylon (202) comprising an air-oil exchanger system (30) arranged in an inter-ducts compartment (22) b...
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WO/2020/115403A1 |
Solid booster (14) for a launcher, the booster being suitable for being separated from the rest of the launcher and comprising a wall (18) defining a combustion chamber (19) comprising an end, termed a front end (19a), and an opposite en...
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WO/2020/115397A1 |
The device (1) for damping a fluid intended for a reservoir (6) in particular of a spacecraft comprises a framework (3) provided with at least one ring (8) and with a plurality of rods (7), each of said rods (7) being fastened by a first...
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WO/2020/115424A1 |
The invention particularly relates to a thrust reverser (1) comprising a fixed (2) and mobile (3) structure defining an air stream, a flap (4) comprising a single wall (40) perforated on the surface thereof, and comprising a structure (4...
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WO/2020/055220A9 |
A self-propelled vehicle which can be configured in the form of an aircraft and comprises a central system of compartments, working members, and a drive comprising the following components: a source of energy, a transmission mechanism, c...
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WO/2020/109705A1 |
The invention concerns a turbofan engine comprising an exhaust casing (21) traversed by a primary flow (FP) and surrounded by a secondary flow (FS) and an outlet cone (23) carried by this exhaust casing (21), the exhaust casing and the o...
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WO/2020/111622A1 |
The present invention relates to a hybrid rocket engine using an electric motor-driven oxidizer pump, wherein an overheated electric motor and battery are cooled by a low temperature oxidizer, and pressure generated from the vaporization...
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WO/2020/107844A1 |
An infrared enhancer with controllable radiation power, relating to the field of unmanned aircraft, and capable of solving the problem of the difficulty of controlling the radiation power of infrared enhancers. The infrared enhancer comp...
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WO/2020/112200A2 |
A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, ...
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WO/2020/109706A1 |
The invention relates to a turbojet engine comprising a central shaft (AC) surrounded by a coaxial and independent high-pressure body (CH), said turbojet engine comprising, from upstream (AM) to downstream (AV): - a fan (13) driven by th...
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WO/2020/097608A1 |
A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. ...
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WO/2020/093578A1 |
Provided is an engine of an aircraft. The engine comprises an outer casing (1), an inner casing (2), a first rotating shaft (3), a first fan (4), a second fan (5), a first combustor (6) and a second combustor (7). An outer duct (100) is ...
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WO/2020/094972A1 |
The present invention relates to a sealing joint (105) for an aircraft turbojet engine nacelle, the joint comprising a bead (115) designed to be mounted in a joint support. According to the invention, the sealing joint is characterised i...
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WO/2020/091738A1 |
An injector for a liquid rocket engine includes an array of injector elements. Each injector element includes a central passage and a plurality of peripheral transverse passages. The central passages are configured to provide axial injec...
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WO/2020/089344A1 |
The invention relates to a blade (3) of a fan (1) of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement (4) obtained by means of the three-dimensional weaving of strands and a matrix in...
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WO/2020/086568A1 |
By manipulating the fluid flow in the proximity of an object such as a fuselage, a wing, or the hull of ship, the wave drag associated with this object can be substantially reduced. This can be accomplished by locally changing both the f...
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WO/2020/084248A1 |
The invention relates to a de-icing device designed to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising: - the separation nozzle which is designed to be positioned d...
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WO/2020/084270A1 |
The invention concerns an aircraft turbomachine, comprising a fan (12) that is able to rotate inside a casing (40), and an electric machine comprising a rotor (60) secured to the fan and a stator (66) secured to the casing (40), characte...
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WO/2020/084271A1 |
The invention concerns an aircraft turbomachine comprising an outer housing (2) delimiting, with an inner hub (3), a flow path (1) for a gas stream in which a low-pressure turbine is arranged, configured to rotate a low-pressure shaft; t...
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WO/2020/084221A1 |
The invention relates to an electric module (11) of a fan of axis A, comprising a fan (12) provided with blades (13) which are rotatably movable inside a casing (40), and an electric machine comprising a rotor (60) secured to the fan (12...
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WO/2020/084245A1 |
The invention relates to an aircraft propulsion assembly (1) comprising a turbojet engine (5), comprising a fan case (45), a nacelle (3) and a suspension pylon, said nacelle comprising a downstream section of D-shaped structure containin...
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WO/2020/078720A1 |
A method for controlling a turbomachine (T) comprising an electric motor (ME) forming a torque injection device on a high-pressure rotation shaft (22), in which method a fuel flow setpoint QCMD and a torque setpoint TRQCMD provided at th...
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WO/2020/079419A1 |
The present invention relates to a multi-source aircraft propulsion arrangement comprising a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may ...
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WO/2020/074304A1 |
A method and device for driving vehicles (land, water, air) around which gaseous or liquid fluids flow having a fuselage or hull and a jet propulsion system, composed of at least one front propulsor P1 and at least one rear propulsor P2,...
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WO/2020/073683A1 |
A separable combined range-extending system and method for an aircraft. A rocket range-extending module, a base bleed range-extending module, a roll range-extending module and a glide range-extending module are all arranged in the system...
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WO/2020/074839A1 |
The invention relates to a fan module (3) comprising variable-pitch blades, said fan module (3) including: a fan rotor (20) bearing the blades (23) of the fan (4, 400a, 400b), each mounted to pivot about a pitch axis (A); a fan shaft (21...
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WO/2020/074817A1 |
Disclosed is a turbine engine (1) comprising: - a rotor (3) having at least one variable-pitch blade (5) which is guided to rotate on bearings (6, 7) relative to a fixed structure (4); - a system (8) for controlling the pitch of the at l...
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WO/2020/076975A1 |
Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and ...
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WO/2020/076187A1 |
The invention relates to quantum electronics, specifically to methods of generating radiation in gas-dynamic flow lasers and can be used in creating process gas-dynamic laser systems integrated into the structure of a gas-turbine engine....
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WO/2020/074816A1 |
The invention relates to a turbine engine (1) comprising: a rotor (3) supporting a blade (5) and guided by means of bearings (6, 7); a control system for controlling the blade (5), which is solidly connected to the rotor (3) and which co...
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WO/2020/068650A1 |
The subject matter of this specification can be embodied in, among other things, a fuel delivery component, including a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defi...
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WO/2020/065182A1 |
The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11), the second shaft (16) being rotated by a third shaft (9) of a ...
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WO/2020/068914A1 |
Methods and systems for nacelle door electromechanical actuation may include a power distribution unit comprising a motor and differential gears; and a plurality of electromechanical actuators, each coupled to an output of a correspondin...
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WO/2020/068838A1 |
A hybrid jet engine, including a connected front and rear cowling having a tubular shape, such that the rear cowling is smaller than the front cowling, a central core and longitudinal shaft disposed within the front cowling and the rear ...
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WO/2020/065473A1 |
The present invention relates to an improved jet engine. The engine incorporates an inner chamber (102) that is enclosed within an outer chamber (104) of the engine (100). An inlet system (108) feeds jet fuel and air/oxygen/chemical oxid...
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WO/2020/068644A1 |
The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the...
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WO/2020/058607A1 |
A turbofan engine nacelle comprising a thrust reverser system provided with at least one movable cowl (8) retracting towards a rear reverse-jet position, tilting pivoting flaps (10) which at least partially close an annular flow duct (18...
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WO/2020/058650A1 |
The invention concerns acoustic management on an aircraft turbine engine (3, 12) or on a nacelle (1, 10) by means of a panel (30, 32). On a support (38), an indentation (34) is provided that is recessed relative to a general surrounding ...
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WO/2020/058651A1 |
The invention relates to acoustic management, on a turbomachine of an aircraft or on a nacelle, via a panel (30, 32). On a support (38) there is reserved a recess (34) that is set back relative to a surrounding general surface (36) in co...
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