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Matches 1 - 50 out of 9,922

Document Document Title
WO/2021/008900A1
The invention regards a gas turbine engine for an aircraft that comprises a nacelle (112), a fan (102), an engine core located downstream of the fan, the engine core comprising a turbine and a core shaft (111) coupling the turbine to the...  
WO/2021/010810A1
A fuel discharge system for a reaction engine having a single-stage or multi-stage dynamic gas compressor is provided with stoichiometric pairs of nozzles and/or tangentially offset pairs of nozzles and/or nozzles for feeding a catalyst ...  
WO/2021/009953A1
Provided is a gas turbine system 100 equipped with: a compressor (10) that compresses external air to generate compressed air; a combustor (20) that burns the compressed air generated by the compressor (10) with fuel to generate combusti...  
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...  
WO/2020/234525A3
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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 ...  
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...  
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;...  
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,...  
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,...  
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...  
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...  
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...  
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...  
WO/2020/181117A8
To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant in...  
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...  
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.  
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...  
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...  
WO/2020/188200A3
The invention relates to a nacelle (10A) for an aircraft bypass turbomachine (100), comprising: •an annular envelope (11) extending about a longitudinal axis (104), • a thrust reverser (13) comprising: • an annular movable cowl (14...  
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...  
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...  
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...  
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...  
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...  
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...  
WO/2020/183074A3
The invention relates to a turbine comprising a first rotor (22a) and a second rotor (22b) that can turn in opposite directions and intermesh. The turbine also comprises a ring (66) to which abradable material (68) is fixed, the ring (66...  
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...  
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...  
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...  
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 ...  
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...  
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, ...  
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...  
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...  
WO/2020/208318A1
The invention concerns a hybrid propulsion installation (100) for an aircraft, comprising: an internal combustion engine comprising at least one combustion chamber (114); at least one electricity generator (134a, 134n); an electrical pro...  
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...  
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...  
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...  

Matches 1 - 50 out of 9,922