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WO/2019/140029A1 |
The subject matter of this specification can be embodied in, among other things, a turbofan engine assembly includes a engine, a nacelle defining a generally forward-to-aft bypass air flow path, a thrust reverser comprising a first movab...
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WO/2019/135058A1 |
The invention relates to a structure (131) for the nacelle of an aircraft propulsion unit, comprising a first skin and stiffeners (3) arranged to hold acoustic treatment modules (4) against the first skin. Each acoustic treatment module ...
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WO/2019/129983A1 |
The invention relates to a method for producing a part made from a composite material, comprising the following steps: formation of a fibrous texture (10) using refractory ceramic fibres; placement of the fibrous texture (10) in a mould ...
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WO/2019/127936A1 |
Provided are a nozzle structure, a jet device and an engine. The nozzle structure (2) comprises: a nozzle body (10), the nozzle body (10) being provided with a liquid flow channel (11), with a first end of the liquid flow channel (11) be...
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WO/2019/129961A1 |
The invention concerns a grid-type thrust reverser (22) for a turbojet engine, the reverser comprising a moving O-shaped thrust reverser body (30) that is generally cylindrical in shape around a longitudinal central axis (A) and that com...
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WO/2019/121022A1 |
The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle comprising: a propelling nozzle wall (20), a duct (15), which is radially outwardly bounded by the propelling nozzle wall ...
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WO/2019/122657A1 |
A guide vane (15) in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis (Iz) of the vane (15) so that the differential thermal expansions compensate for the bending de...
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WO/2019/122753A1 |
The invention relates to a nacelle for a turbofan, comprising a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls (6, 8), said cascades moving rearwards with movab...
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WO/2019/122761A1 |
The present invention relates to a propulsion unit (5) for an aircraft, comprising: a nacelle (7), a turbojet engine (1), an annular passage (19) for a secondary air flow, and a pre-cooler device (3) in communication with an engine enclo...
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WO/2019/122752A1 |
The invention concerns a nacelle of an aircraft turbofan engine comprising an air inlet (2) upstream from the engine, a median section (4) intended to surround a fan (5) of the engine and delimited on the outside by a fan cowl (6) suppor...
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WO/2019/121148A1 |
The invention relates to a thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle comprises a thrust nozzle wall (20), and a flow channel (25) that is delimited radially outwards by the thrust nozzle wall...
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WO/2019/115960A1 |
The present invention concerns a propulsion unit for an aircraft, comprising a nacelle with a D-shaped structure housing a thrust-reversing device with movable vanes, the nacelle comprising two D-shaped half-structures (117a, 117b) each ...
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WO/2019/116008A1 |
A variable area fan nozzle for a turbofan aircraft engine is described. The variable area fan nozzle comprises a first structure defining a forward portion of a bypass duct of the turbofan aircraft engine and a second structure defining ...
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WO/2019/118259A1 |
A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a no...
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WO/2019/110889A1 |
Assembly for a rocket engine diverging nozzle section, comprising a rocket engine diverging nozzle section having an outer wall and an axis of revolution, a plurality of heat shield blocks which are made of a thermally insulating materia...
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WO/2019/110888A1 |
Assembly for a rocket engine diverging nozzle section, comprising a rocket engine diverging nozzle section having an outer wall, a plurality of heat shield blocks made of a thermally insulating material, said blocks being designed to be ...
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WO/2019/112649A1 |
A flight vehicle engine includes an isolator with a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where t...
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WO/2019/106298A1 |
The invention relates to a thrust reverser (30) for a nacelle (1) of an aircraft engine (6), the thrust reverser (30) comprising a movable cover (31) which moves back from a closed position in which the thrust is not reversed to an open ...
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WO/2019/105496A1 |
The invention relates to a component of a flow machine and to a method for producing a component of a flow machine, in particular a gas turbine or an aircraft engine, wherein the component is formed from a fibre-reinforced material, in p...
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WO/2019/108306A1 |
A rocket engine includes a copper alloy combustion chamber, a non-copper weld transition ring welded to the copper alloy combustion chamber, and an injector assembly welded to the non-copper weld transition ring. The engine can be manufa...
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WO/2019/106312A1 |
An auxiliary solid propellant booster (100) intended to be attached to the main body of a launcher comprises a cylindrical body (110) extending in a longitudinal direction (X-X') between a back end (120) in communication with a nozzle (1...
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WO/2019/102170A1 |
Turbojet engine nacelle comprising a cascade-type thrust reverser comprising a mobile circular frame surrounding a cold air flow path, guided axially by longitudinal rails (8a, 8b) fixed to an intermediate casing (10) surrounding the col...
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WO/2019/097170A1 |
The invention relates to an aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser with cascades of mobile deflection vanes (43). The cascades of deflection vanes (43) are connected to cascade rails (45)...
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WO/2019/097159A1 |
Disclosed is a pipe/flange assembly intended for use with a pressurization system of an aeronautical vessel, said assembly comprising a flange (10) having a main part (12) with an orifice (11) and a sleeve (14) projecting from the main p...
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WO/2019/098473A1 |
The present invention relates to a partial structure of a rocket, which includes a satellite launcher engine and an auxiliary engine added thereto, to enable continuous ignition by a spark method, and more specifically, proposes a contin...
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WO/2019/092383A1 |
The present invention relates to a thrust reverser (6) for a turbojet engine nacelle (1), comprising at least one movable cover (20) mounted on a fixed structure of the reverser (6), moveable between a closed position, in which it ensure...
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WO/2019/086616A1 |
The present invention relates to a swirling element for swirling a fluid flow for a rotating aerodynamic profile or a turbine, comprising: a fastening portion, which is designed for fastening to a profile surface; and a flow-active porti...
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WO/2019/086647A1 |
A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: ∙ a combustion chamber (21), ∙ at least one feed line for feeding a flowable, explosive material or components which...
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WO/2019/081865A1 |
The lock for a cowl (1) of a thrust reverser borne by a nacelle (4) comprises: a catch (16) fixed on the cowl; and a hook (12) that is configured to engage in the catch and is elastically returned (15) towards engagement with the catch; ...
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WO/2019/081864A1 |
The invention relates to a propulsion unit (1) for an aircraft, comprising a nacelle (2) comprising a turbojet (8) supported by a pylon (3), the nacelle (2) comprising: an outer shroud (9), a fixed internal structure (4) defining, with t...
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WO/2019/077365A1 |
An emergency landing apparatus (100) for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors (30) arranged to eject efflux in order to pr...
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WO/2019/079137A1 |
A control system for a satellite comprises a power source and control system, a propulsion system having individually selectable solid fuel motors, a communication interface and an attitude determination and control system (ADCS). The AD...
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WO/2019/076524A1 |
The invention relates to an injector (1) for metering liquid and gaseous fuel, comprising an injector body (2) in which a pressure chamber (3) is formed that can be filled with gaseous fuel, wherein a piston-shaped outer nozzle needle (5...
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WO/2019/075051A1 |
A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In an...
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WO/2019/071289A1 |
A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocke...
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WO/2019/073436A1 |
An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing...
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WO/2019/073437A1 |
A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (2...
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WO/2019/073167A1 |
The invention relates to thermal protection (18) comprising, superposed on one another in order, a metal plate, a first layer of insulating material, a layer of refractory fibres, and a second layer of insulating material, the metal plat...
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WO/2019/068996A1 |
The invention concerns the production in composite material of a lobed structure (10) of a mixer, which comprises a portion having a plurality of lobes (17,19). For this purpose, a fibrous preform is produced containing a resin, in a sim...
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WO/2019/069306A1 |
A pulsejet engine is provided, comprising a combustion chamber spanning between an inlet and end and an outlet end for combustion therein of a mixture of fuel and air, an intake regulator configured to selectively open and close one or m...
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WO/2019/063938A1 |
The invention relates to an assembly having a holder (10) configured to be fastened to a spacecraft, a thruster, a damping device (50), the damping device (50) having at least two electrodes (50b) and at least one electroactive polymer (...
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WO/2019/063935A1 |
The invention relates to an injection wall (10) for a rocket engine combustion chamber, said wall being provided with a plurality of injection orifices (20), wherein the majority of said injection orifices (20) are arranged in an asymmet...
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WO/2019/063939A1 |
The invention relates to an assembly having a holder (10) configured to be fastened to a spacecraft, a thruster, an orientation device (40) having at least one actuator (44) that is able to modify the orientation of the thruster, the act...
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WO/2019/058054A1 |
A method for producing a part from composite material comprises the following steps: - injecting into a fibrous texture (10) a slurry (BC) comprising at least one powder of refractory ceramic particles (CR) suspended in a liquid phase, -...
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WO/2019/059401A1 |
The three-dimensional additively-formed product comprises: a body section; and a male threaded part integrally formed with the surface of the body section in a projecting manner. The male threaded part has a trailing flank forming a firs...
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WO/2019/058069A1 |
The invention relates to a method for manufacturing a part using CMC, i.e. a ceramic matrix composite material, as well as such a part made of CMC, the method comprising the following steps: providing (E1) a fibrous reinforcement (10); i...
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WO/2019/052886A1 |
In an exhaust gas duct for exhaust gases of gas turbines (1) having a housing (6) made of metal, an inner lining (30) made of metal and supported by the housing (6), and insulation (9) arranged between the housing (6) and the inner linin...
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WO/2019/050511A1 |
An internal combustion engine with a piston having a piston head with a resonance cavity opening onto the head, and where a fuel nozzle located in a cylinder head is positioned to inject a fuel such as natural gas into the combustion cha...
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WO/2019/045997A1 |
A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rota...
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WO/2019/045669A1 |
A pulsed compressive detonation device comprises a piston compressor (1) consisting of at least a cylinder (2) that houses a piston (3) provided with a reciprocating motion actuator (4), an intake manifold (6) connected to the cylinder (...
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