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WO/2021/005306A1 |
The invention relates to an assembly intended for retaining a gear train in a turbomachine, the assembly comprising an annular casing (44) in which is engaged an annular part (48) that is prevented from rotating in the casing (44) by ann...
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WO/2021/001527A1 |
The present invention relates to a propulsion assembly for an aircraft, comprising a coupled-turbine turbomachine comprising a combustion chamber and a shaft that is mounted so as to rotate and is designed to rotate at a turbomachine rot...
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WO/2020/263104A1 |
Drive shaft monitoring system (20) comprising a first and second coded disc (21a-b), wherein the first (21a) and second (21b) coded disc are provided with multiple slots or recesses (22) evenly distributed in circumferential direction th...
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WO/2020/257649A1 |
Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliv...
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WO/2020/249896A1 |
The invention relates to a thrust reverser (12) for an aircraft propulsion unit, this thrust reverser (12) comprising an internal fixed structure (13), a mobile cowl (16) and blocking flaps (17). The thrust reverser (12) comprises a firs...
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WO/2020/245553A1 |
The invention relates to a thrust group (300) for a propulsion device (10), comprising a thrust engine (302), arranged to provide a thrust force (F1, F2) oriented in a direction so as to provide substantially vertical take-off and landin...
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WO/2020/245516A1 |
The invention concerns a method for regulating the acceleration of a turbomachine, the turbomachine comprising a combustion chamber, a high-pressure turbine situated downstream from the combustion chamber and that rotates a high-pressure...
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WO/2020/245525A1 |
The invention relates to a confluence structure of an aircraft bypass turbine engine which comprises a confluence plate (13) with a downstream end (16) supported by a portion (20) that is movable in the direction of the axis (X) by a con...
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WO/2020/245388A1 |
The invention relates to an aircraft (1), in particular an aircraft with support surfaces (11, 12), comprising a hull (10) for receiving at least one pilot and/or a payload, in particular air freight and/or at least one passenger, and at...
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WO/2020/245390A1 |
The invention relates to an aircraft and to a method for operating an aircraft (1), in particular an aircraft with support surfaces (11, 12), comprising a hull (10) for receiving at least one pilot and/or a payload, in particular air fre...
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WO/2020/245513A1 |
The invention relates to a thrust unit (300) for a propulsion device (10), comprising a thrust motor (302), arranged to provide a thrust force (F1, F2) oriented in a direction so as to provide substantially vertical take-off and landing ...
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WO/2020/245379A1 |
The invention relates to an aircraft (1) and to a method for operating an aircraft (1), in particular an aircraft with support surfaces (11, 12), a hull (10) for receiving at least one pilot and/or a payload, in particular air freight an...
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WO/2020/239870A1 |
Disclosed is an aircraft propulsion assembly (1) comprising a nacelle and a turbojet engine, the nacelle comprising an outer casing (5) comprising fan cowls (4) and the turbojet engine comprising at least one fan casing (6, 6'), the fan ...
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WO/2020/239899A2 |
An engine comprises an air intake arrangement configured to receive air; a heat exchanger arrangement arranged downstream of the air intake arrangement, configured to cool the air, and comprising a plurality of heat exchanger modules; an...
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WO/2020/234524A1 |
The invention relates to a heat exchange system (20) for a turbomachine, comprising a heat exchanger (21) that comprises a support wall (22; 54; 53) that extends substantially along a longitudinal direction L and a plurality of fins (23;...
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WO/2020/030858A9 |
The invention concerns an assembly for an aircraft turbojet engine, comprising a central gas ejection element (1), and a connecting flange (9) interposed between, in the upstream direction, a metal outlet (22a) of a turboject engine and,...
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WO/2020/236961A1 |
An electrospray apparatus including a plurality of emitters, disposed on a substrate, wherein the plurality of emitters can have a narrow parameter distribution, and where the apparatus can optionally include one or more control systems,...
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WO/2020/234545A1 |
Space launcher comprising a turbopump (30), a heat exchanger (40) and an exhaust nozzle (50) which are arranged in a fluid-flow exhaust duct (20), from upstream to downstream in a direction of fluid flow in said exhaust duct (20), the he...
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WO/2020/234540A1 |
Space launcher comprising a launcher body (1), an engine (2), a combustion chamber (4), a nozzle (5) having a main axis (Z-Z), the nozzle (5) being provided with a plate (6) extending radially, the plate (6) having an inner face and an o...
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WO/2020/234525A2 |
The invention relates to a heat exchange system (20) of a turbomachine, comprising a heat exchanger (21) comprising a support wall (22; 54; 53), a plurality of fins (23; 230; 230a; 230b) each extending in a radial direction from a radial...
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WO/2020/234539A1 |
Space launcher comprising a launcher body (1), an engine (2), a nozzle (5) provided with a plate (6) extending radially around the nozzle (5) or a combustion chamber (4) and insulating an internal volume of the spacecraft from an externa...
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WO/2020/229763A1 |
Acoustic cowl (20) for a turbomachine or an aircraft propulsion assembly, this cowl having a shape that is annular about an axis and comprising two annular skins, these respectively being radially internal and radially external skins, ex...
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WO/2020/229305A1 |
The invention concerns an airflow arrangement for a gas turbine engine in which air can be selectively directed to and from a bypass channel of the engine and into a duct communicating air into a compressor of a gas turbine engine.
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WO/2020/229232A1 |
The invention relates to a door (13) for a thrust reverser (12) of a propulsion assembly, the door being provided with a flexible baffle (19). Said baffle (19) is configured to change state by moving from a folded position to an unfolded...
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WO/2020/224890A1 |
The invention relates to a turbine engine separate flow mixer (2) centred on a longitudinal axis (X-X), comprising an exhaust housing (6), a shroud (4) directly connected to the exhaust housing (6) and intended to mix the flows originati...
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WO/2020/224887A1 |
A cascade (80) for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade (80) comprising first partitions (82) extending in a first direction (DA), second fixed partitions (83) extending in a secon...
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WO/2020/224889A1 |
Disclosed is a cascade-type thrust reversal device for a turbomachine (1) of an aircraft, comprising a cascade (80) having first partitions (82), second partitions (83) intersecting the first partitions (82), and cavities (84), and a cas...
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WO/2020/224888A1 |
A cascade-type thrust reversal device (70) for a turbomachine (1) of an aircraft, comprising a thrust reversal cascade (80) and a casing (71), the cascade (80) having first cavities (84) and the casing (71) comprising an opening (76) def...
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WO/2020/224886A1 |
A cascade (80) for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade (80) comprising first partitions (82) extending in a first direction (DA), second partitions (83) extending in a second dire...
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WO/2020/227237A1 |
An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the...
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WO/2020/221976A1 |
Acoustic treatment panel (10) intended to be disposed on at least one wall of a jet engine (1) in contact with a fluidic flow, the panel (10) comprising a first sheet (16), a second sheet (14) that is parallel to the first sheet (16) and...
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WO/2020/222667A1 |
The present application relates to a sound insulating panel, suitable for use as a deflecting surface in jet blast deflectors. Therefore, it is described a jet blast deflector fence, comprised of detachable sound insulating panels, formi...
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WO/2020/212232A1 |
Method for using an air intake (2) of a turbojet engine (1) nacelle comprising at least one elastically deformable portion (230), at least one connecting member (3) mounted in an annular cavity (20) integrally with the elastically deform...
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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/2020/212561A1 |
The invention proposes a method for manufacturing a grid for a cascade-type thrust reverser of a jet engine, the method comprising the following steps: a) manufacturing a first component comprising continuous or long fibres pre-impregnat...
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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/2020/212396A1 |
The invention relates to an injector device for an engine device for introducing a fluid fuel, in particular a liquid fuel, and a fluid oxidant, in particular a liquid oxidant, into a combustion chamber of the engine device, which inject...
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WO/2020/201522A1 |
The present invention concerns a method for monitoring an actuating system of a movable component, in particular a movable component of a turbomachine such as a nozzle or a blade, the actuating system comprising a control device configur...
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WO/2020/201034A1 |
The invention relates to an engine nacelle (100) for a turbojet engine of the type comprising a lubricant (H), the nacelle comprising a cooling system comprising: - at least one exchanger (14), referred to as the cold source exchanger, b...
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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/2020/202867A1 |
A high-temperature component according to one embodiment requires cooling performed via a cooling medium, wherein: the high-temperature component comprises a plurality of first cooling passages through which the cooling medium can flow, ...
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WO/2020/201644A2 |
The present invention relates to the field of aeronautics and more particularly to a high-lift device and an aerodyne comprising such a high-lift device and an aircraft safety device (ASD). The present invention relates to a novel high-l...
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WO/2020/193926A1 |
The invention relates to a method for removing webs (2) formed on a wall (12) of a central canal (11) of a solid-propellant charge (1), characterized in that the method comprises a step (110) of removing webs (2) by shaving the wall (12)...
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WO/2020/196579A1 |
A laser ignition device (1) is provided with an excitation light source (2) for generating excitation light, and a pulsed laser oscillator (4) connected to the excitation light source, wherein the pulsed laser oscillator generates a plur...
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WO/2020/193905A1 |
The invention relates to a counter-rotating turbine (22) of an aircraft turbomachine (10), comprising: - a casing (34) comprising an endoscopy port (40) configured for an endoscopy plug (58) of a non-destructive testing device (60) to pa...
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WO/2020/193925A1 |
A jet nozzle (100) comprises a combustion chamber (110) which has a downstream end (111) and a divergent nozzle section (120) made of a cone-shaped wall (121) extending between an upstream end (122) and a downstream end. The upstream end...
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WO/2020/193919A1 |
Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third turbomachine control quantity, each of which can become saturated as a function of the turbomachine operating ...
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WO/2020/195792A1 |
Provided is a canned motor in which gasification of a liquid being handled, occurring when a rotor is rotating at high speed, is reduced. A canned motor 10 includes: a stator 18 disposed in a stator chamber 26; a rotor 14 disposed in a r...
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