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Patent Searching and Data


Matches 1 - 50 out of 9,541

Document Document Title
WO/2019/136535A1
The present device for redirecting and lending momentum to streams of a fluid under pressure is positioned at the outlet of an external power device that generates propulsive thrust, such as a pump, a turbine, a propeller, or functional ...  
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...  
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 ...  
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 ...  
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...  
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...  
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 ...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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 ...  
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...  
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...  
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 ...  
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...  
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 ...  
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...  
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...  
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...  
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...  
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)...  
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...  
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...  
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...  
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...  
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...  
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; ...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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 (...  
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...  
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...  
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, -...  
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...  
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...  
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...  
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...  
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...  

Matches 1 - 50 out of 9,541