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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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WO/2020/058652A1 |
Double-flow turbo-reactor (10) comprising a blower (20), a casing (30) which is arranged downstream of the blower (20) and which separates a main jet (12) from a secondary jet (14), a compressor (60), a combustion chamber (70) and a turb...
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WO/2020/058653A1 |
Turbojet (10) comprising a blower (20), a compressor (60), a combustion chamber (70) and a turbine (80) which is configured to rotate the blower (20) via a first step-down mechanism (40) and to rotate the compressor (60) via a second ste...
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WO/2020/055579A1 |
A barrier coating resin formulation comprising at least one polycarbosilane preceramic polymer, at least one organically modified silicon dioxide preceramic polymer, at least one filler, and at least one solvent. A barrier coating compri...
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WO/2020/055625A1 |
A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as...
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WO/2020/053672A1 |
A propeller's or rotor's blade has as main functions the reduction of the pressure behind a turbine and the production of lift. There is a suction side and a higher-pressure side on the blade. This pressure gradient is used to produce li...
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WO/2020/049090A1 |
The present invention relates to a propulsion system for a spacecraft comprising at least one chemical propulsion engine, at least one electrical propulsion engine; and, a propellant feed system comprising: a propellant supply system inc...
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WO/2020/049256A1 |
The invention relates to an assembly for a turbomachine of longitudinal axis comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending in a manner radially facing said first annular w...
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WO/2020/049258A1 |
Thrust reverser for an aircraft propulsion assembly, this thrust reverser comprising a movable structure provided with external covers (411) connected to hinges (51) through a pivot connection allowing the external covers (411) to rotate...
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WO/2020/050689A1 |
Provided is a propulsion device for a liquid propellant rocket engine according to an embodiment, comprising: a main body into which a liquid propellant is introduced; an injector core located inside the main body; at least one outlet co...
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WO/2020/049091A1 |
The present invention relates to a propulsion system for a spacecraft comprising at least one electrical propulsion engine comprising at least one neutraliser; and a pressurant gas system comprising a pressurant gas; wherein the pressura...
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WO/2020/049528A1 |
An example engine for producing thrust includes: a fuel supply to supply a fuel; a chamber fluidly coupled to the fuel supply to receive the fuel; an induction heating assembly operatively coupled to the chamber to inductively energize t...
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WO/2020/043977A1 |
A duct for evacuating hot air (4) from an aircraft engine is extended by a movable stack (13) that can project from the wall (1) such that the hot air is ejected a distance from the wall (1) without risk of damaging the wall. The stack (...
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WO/2020/044018A1 |
A structure comprising a nacelle or a thrust reverser, the structure comprising a stationary part and a movable part, the structure comprising: a first guide provided on or in the stationary part of the structure or the movable part of t...
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WO/2020/038887A1 |
The invention relates to an architecture (1) for controlling and/or monitoring at least one actuator (2a, 2b) of a mobile cowl (3a, 3b) of a thrust reverser (4) equipping a nacelle, the actuator (2a, 2b) being driven by at least one engi...
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WO/2020/041675A1 |
A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference...
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WO/2020/036506A1 |
The present invention is a device for generating thrust. Said device is intended for producing thrust and can be used in industry, primarily in transport. In order to generate thrust using centrifugal force, a section of a pipe for movin...
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WO/2020/036618A1 |
An inlet duct (17) for use with an engine (33) is presented. The invention includes a duct structure (38), at least one spike (19) disposed along an interior surface (18) of the duct structure (38), and an inlet throat (34) formed by one...
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WO/2020/030874A1 |
The invention relates to a system for cooling a fluid of a lubrication circuit (20) of a propulsion engine (10) of an aircraft comprising a nacelle (11) which extends in a longitudinal direction (X) between an air inlet (12) and an eject...
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WO/2020/025895A1 |
The invention relates to an annular heat exchanger (12a) having a longitudinal axis (L) for a turbomachine, intended, for example, to be supported by an annular ferrule of a housing of the turbomachine, comprising an annular one-piece pa...
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WO/2020/025528A1 |
The invention relates to a drive system for an, in particular electrically driven, aircraft. The drive system is provided with thrust measuring means which measure a currently effective thrust of the thrust generator of the aircraft. The...
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WO/2020/021199A1 |
The invention relates to a turbomachine blade having a turbine blade airfoil (12) extending in a first direction between a leading edge (18) and a trailing edge and in a second direction, which is substantially perpendicular to the first...
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WO/2020/016520A1 |
The invention concerns a method for manufacturing a composite panel, in particular in a turbomachine, characterised in that it comprises the following steps: a) producing a first wall, a second wall, a third wall and a fourth wall from c...
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WO/2020/017990A1 |
The invention relates to the field of rocket technology, specifically to a propellant consumption control system. A system for the combined control of propellant consumption for a rocket propulsion unit comprises propellant flow-rate sen...
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WO/2020/018565A1 |
A three-dimensional monolithic diaphragm tank including a first portion having a first inner surface, a second portion having a second inner surface, and a deformable diaphragm extending from a peripheral junction with the first inner su...
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WO/2020/012971A1 |
A readily combustible portion (110) has a readily combustible exposed surface (111) exposed in a flow channel (CA). A combustion-resistant portion (140), which comprises a material that does not burn as readily as the readily combustible...
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WO/2020/010109A1 |
Systems, apparatus, and method for manufacturing are disclosed. In an aspect, the apparatus may be a cold-spray nozzle. The cold-spray nozzle may include a variable diameter convergent part. The cold-spray nozzle may also include a varia...
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WO/2020/008147A1 |
The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having...
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WO/2020/007847A1 |
A turbomachine for an aircraft extending axially along an axis X comprising a primary flow path in which an air stream flows intended for the combustion chamber (102) and a secondary flow path in which an air stream flows intended for pr...
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WO/2020/010098A1 |
Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is ...
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WO/2019/241898A1 |
The invention relates to stationary gas turbines, characterised in that the air mass flow after the low-pressure compressor is divided into multiple parallel sub-flows, which are supplied to the low-pressure expansion turbine via two or ...
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WO/2019/243767A1 |
An electric engine comprises: an inner casing; an outer casing which is positioned around the inner casing; a rotor comprising a plurality of rotor blades, the rotor being located between the inner and outer casings and being rotatable a...
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