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WO/2020/216713A1 |
The present application relates to an air intake (2) for a turbojet engine nacelle comprising an annular structure (21, 22) and a rear bulkhead (23), the annular structure (21, 22) comprising at least one portion (21A) of an outer shroud...
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WO/2020/217027A1 |
The invention relates to an air intake for an aircraft engine nacelle, the air intake comprising a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, a front mounting flange conf...
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WO/2020/217025A1 |
The invention relates to an air intake (3) for a nacelle (1) for an aircraft engine (6), the air intake (3) comprising a front lip (31) connecting a substantially cylindrical internal wall (32) and a substantially cylindrical external wa...
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WO/2020/216712A1 |
The invention relates to an air intake (1) of a turbojet engine nacelle comprising an annular structure (110) including an outer fairing (100) defining an aerodynamic outer surface and an inner fairing (102) defining an aerodynamic inner...
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WO/2020/212225A1 |
A process for using an air input (2) of a turboreactor nacelle (1) of an aircraft, comprising an air input lip (23) which comprises at least one fixed portion and at least one portion (3, 3', 4, 4', 5, 5', 6, 6', 7) which can be moved be...
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WO/2020/212224A1 |
An aircraft turbojet engine (1) extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake (2) which comprises at least one deflection member (3, 4, 5) movably mounted ...
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WO/2020/212226A1 |
An aircraft turbojet engine (1) comprising a fan (11) configured to provide a reverse thrust and a nacelle comprising an air intake (2), the air intake (2) comprising at least one circulation duct (3) in the annular cavity (20) opening, ...
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WO/2020/212228A1 |
Disclosed is a method for using an aircraft turbojet engine (1) comprising an air inlet (2) comprising a plurality of rectifier vanes (3), each rectifier vane (3) being mounted such that it can move between a retracted position to assist...
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WO/2020/201652A1 |
The invention concerns a method for monitoring at least one aircraft engine, said method comprising an acquisition (100) depending on first and second sets of measurements of respectively endogenous and exogenous variables. The method al...
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WO/2020/201033A1 |
The invention concerns a method for manufacturing a structural surface heat exchanger of preset or left-hand final shape (10) for an aircraft, comprising the steps of forming (E1), shaping (E2; E3) and assembling (E4), by welding or braz...
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WO/2020/201658A1 |
The invention relates to an air inlet duct (60) for a nacelle (26) of an aircraft propulsion assembly (10), this duct (60) comprising an annular body (50) and an annular air inlet lip (40) comprising two coaxial annular walls (41, 42), i...
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WO/2020/187345A1 |
The invention relates to an aircraft (3) having at least one wing (32) on which an aircraft propulsion device is arranged which has at least one heat engine (I), in particular a gas turbine (10), and an exhaust gas passage (21) for guidi...
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WO/2020/180377A1 |
A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the...
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WO/2020/180366A1 |
A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected to receive rotational input power from each of the heat en...
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WO/2020/180375A1 |
A power plant a for an aircraft having a hybrid-electric propulsion system including a nacelle body including therein an electric motor directly connected to a gearbox for driving a propeller, wherein the gearbox is connected directly to...
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WO/2020/138076A1 |
An outer plate cooling system is provided with: an outer shell having an outer plate, an inner plate placed inside the outer plate, and a heat insulating layer placed between the outer plate and the inner plate; a cooling chamber which i...
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WO/2020/138075A1 |
This outer panel cooling system comprises: an outer shell having an outer panel and an inner panel; a heat source chamber provided on the inner side of the inner panel; a cooling path provided between the outer panel and the inner panel,...
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WO/2020/136415A2 |
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WO/2020/122077A1 |
[Problem] To provide a motor cooling structure capable of improving cooling efficiency when cooling a motor that has reached a high temperature. [Solution] In the motor cooling structure equipped with a motor disposed on a board and a pr...
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WO/2020/115960A1 |
[Problem] To provide a pressure variation absorbing structure in which it is possible to prevent degradation in pressure variation absorbing performance caused by an air current on a surface and to prevent deviation of a resonance freque...
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WO/2020/113110A1 |
An aerodynamic flow control system in proximity to the nacelle inlet to provide "virtual" shaping of the nacelle's flow surface. The aerodynamic flow control is adjustable so that it can be continuously and adaptively optimized for a ran...
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WO/2020/109482A1 |
The invention relates to a method for customized production of replacement structure parts (40) from a blank (29) for replacing damaged structure components which are provided with a multiplicity of holes for attachment to a receiving st...
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WO/2020/091629A1 |
A twin supersonic convergent air inlet is a supersonic air inlet consisting of two joined, mirror identical parallel supersonic convergent scoop mixed compression air inlets for two engines, said air inlets being fastened to one another ...
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WO/2020/090879A1 |
[Problem] To provide a drone that operates using a fuel cell as a power source and can remain highly safe even during autonomous flight. [Solution] The present invention comprises: a flight control unit 21 that generates thrust by operat...
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WO/2020/084527A1 |
A vehicle (1) provided with an engine (2), at least one air intake (4) through which the engine (2) takes in the external air needed to operate, and an air filter (9) arranged downstream of the air intake (4). The air filter (9) presents...
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WO/2020/075091A1 |
A vehicle (1) provided with an engine (2), at least one air intake (4) through which the engine (2) takes in the external air needed to operate, and an air filter (9), which is arranged downstream of the air intake (4). The air filter (9...
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WO/2020/072365A1 |
The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus (1400) that includes a probe (1410) affixed to an aircraft engine frame and having a shaft (1420) having a barb (1...
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WO/2020/052910A1 |
A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) confi...
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WO/2020/043993A1 |
The invention relates to a handling assembly (31) of a propulsion assembly, comprising a nacelle and an aircraft turbofan, characterized in that it comprises: - a handling envelope (35) covering at least half of the circumference of an o...
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WO/2020/031013A1 |
A heat exchanger (10) for a transmission unit of an aircraft (1) is described that comprises: a first module (23) defining a first feed path (P) for a first fluid to be cooled; a second module (33) defining a second feed path (T) for a s...
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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/2020/008147A1 |
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/2020/005387A1 |
An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted bo...
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WO/2020/001273A1 |
The present utility model relates to a heat dissipation structure and an unmanned aerial vehicle. The heat dissipation structure comprises: a housing; a heat dissipation fan provided inside the housing; and a first air inlet and a second...
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WO/2019/243119A1 |
The invention relates to a rear propulsion system (4) for an aircraft configured to ingest a boundary layer of said aircraft, the rear propulsion system (4) extending longitudinally along an X-axis, the rear propulsion system (4) compris...
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WO/2019/243117A1 |
The invention relates to a rear propulsion system (4) for an aircraft configured to ingest a boundary layer of said aircraft, the rear propulsion system (4) extending longitudinally along an X-axis, the rear propulsion system (4) compris...
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WO/2019/229337A1 |
The outlet (2) of a heat exchange circuit extending under a wall (1), such as a nacelle cowling of an aircraft engine, is divided into openings (7) in the form of parallel slots which are elongated in the longitudinal direction (X) and s...
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WO/2019/232060A1 |
A vehicle includes a main body and at least one wing coupled to the main body. A source of compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster having ...
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WO/2019/224499A1 |
The invention relates to an acoustic attenuation panel (1) for an aircraft jet engine nacelle, and to a method for manufacturing this panel. The panel (1) comprises a central cellular core interposed between an acoustic front skin (3) co...
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WO/2019/220038A1 |
The invention relates to an aircraft power architecture comprising a power transmission gearbox (12), located in a first compartment (30), a gas turbine (14), located in a second compartment (32) comprising a gas generator (18) and a fre...
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WO/2019/202515A1 |
A general mounting method for ducted fan propulsors is disclosed. This mounting method uses extremely slender stators that connect the duct ring to the propulsor which is mounted in the middle and drives the rotor, fan or propeller. The ...
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WO/2019/197224A1 |
A starting/generating system for an aircraft turbine engine, the starting/generating system comprising at least one brushless drive motor/generator (1), at least one control module (6) and at least one power module (7), the power module ...
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WO/2019/192750A1 |
An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel suppl...
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WO/2019/195189A1 |
A Helmholtz resonator having a plurality of resonator chamber modules formed into an array. The array is configured to dampen sound. A module of the plurality of resonator chamber modules includes a first chamber and a second chamber. Th...
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WO/2019/171000A1 |
The invention relates to an active device for attenuating acoustic emissions (8) from a turbojet of an aircraft, characterised in that the device comprises conduits (20) for the circulation of a pressurised air flow supplying rotating el...
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WO/2019/172808A1 |
The invention relates to jet propulsors widely used, for example, in various transport vehicles and is intended for equipping transport vehicles moving in a three-dimensional liquid (for example, in water body) or gas (for example, in...
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WO/2019/166040A1 |
Disclosed is a method for reducing contrails during operation of an aircraft (100, 100') having a heat engine (10). The method comprises: bringing about condensation of the moisture contained in the exhaust gas (A) of the heat engine by ...
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WO/2019/158451A1 |
An acoustic damper (100) for a gas duct system (20), comprises a housing (1) comprising a first wall (2) and a second wall (3) opposite to and spaced from the first wall (2) so as to at least partly define a housing volume there between....
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WO/2019/158884A1 |
The invention relates to a nacelle for a turbomachine, the nacelle comprising an inner wall that is annular about a longitudinal axis of the nacelle, the annular inner wall being designed to surround at least part of the turbomachine, th...
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WO/2019/155175A1 |
The invention concerns a de-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle, characterised in that it comprises an embossed acoustic structure (32) that delimits a plurality of acoustic cells (34), ...
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