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Matches 1 - 50 out of 9,065

Document Document Title
WO/2017/176311A1
A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments in...  
WO/2017/168079A1
The invention relates to a casing (20) for a propellant feed turbopump (10) for a rocket engine (50), comprising a cooling circuit (30), said cooling circuit being arranged at least partially in a wall of the casing (20).  
WO/2017/164773A1
The group of inventions relates to detonation combustion reaction devices. A detonation combustion reaction device contains a ceramic pendulum gate, which is disposed inside a detonation combustion system and divides the system into two ...  
WO/2017/158298A1
The invention concerns a bypass turbojet engine (1) comprising: a low pressure shaft (6) supported by at least two low pressure bearings (BP#1 to BP#4), a high pressure shaft (8) supported by at least two high pressure bearings (HP#1, HP...  
WO/2017/158856A1
A jet engine is provided with an inlet 11 and a combustor 12 having a fuel injection port 30a. The combustor 12 has a wall part 16 that defines an air flow path FA. The wall part 16 has a ramp part 60, which has an inclined face 62, and ...  
WO/2017/158296A1
The invention relates to a turbofan (1) comprising: - a low-pressure shaft (6); - a high-pressure shaft (8); - a fan shaft (7); - a reducing mechanism (10) that couples the low-pressure shaft (6) to the fan shaft (7); and - a maximum of ...  
WO/2017/158294A1
The invention relates to a turbofan engine (1) comprising: a turbine shaft (10); a fan shaft (20); and a reduction mechanism (12) coupling the turbine shaft (10) and the fan shaft (20), said turbofan engine (1) having a bypass ratio grea...  
WO/2017/158857A1
A jet engine is provided with an inlet 11 for taking in air, and a combustor 12 that has a fuel injection port 30a for injecting fuel. The combustor 12 uses the air to combust the fuel injected from the fuel injection port 30a. Between t...  
WO/2017/160375A2
A thruster operable in a chemical mode or in an electrospray mode using the same liquid monopropellant for operation in both modes is described having a multiplicity of a microthrusters made of a catalytic material having a bore therethr...  
WO/2017/153610A1
The invention relates to a ducted propeller (100) comprising a housing (102) with an inlet opening (104) and an outlet opening (106), at least one propeller (108) which is mounted in the housing (102) in a rotatable manner about a rotati...  
WO/2017/153677A1
The invention relates to a rocket engine having more secure and better controlled solar ignition, said rocket engine comprising an axisymmetrical propulsion chamber (12) having a neck (12c) where the diameter of said propulsion chamber (...  
WO/2017/151188A1
A method of producing a propellant material element (12), such as an electrically-operated propellant material, includes extruding a propellant material (16) through a heated nozzle (20). The nozzle may be heated to a temperature that is...  
WO/2017/151189A1
A device may include an electrically-operated propellant or energetic gas-generating material, additively manufactured together with electrodes for producing a reaction in the material. The device may also include a casing that is additi...  
WO/2017/142590A1
A hybrid rocket motor (10) includes a solid fuel element (12), and an oxidizer tank (14) containing an oxidizer (16). The solid fuel element adjoins and at least partially defines a combustion chamber (20) in which the solid fuel and the...  
WO/2017/137740A1
The invention concerns a noise attenuation panel comprising a sound absorbing honeycomb layer disposed between a perforated surface layer on an airflow facing side of the panel and a composite support layer on a second opposing side of s...  
WO/2017/134402A1
The invention relates to a propulsion unit (2) for an aircraft, comprising a turbofan engine (4) comprising an inter-compressor casing (52) which is fixed and is positioned upstream of an inter-channel space (48), a nacelle (6) comprisin...  
WO/2017/134844A1
Provided is an aircraft component used in a gas turbine engine for an aircraft, the aircraft component comprising an annular part having an outer peripheral surface, and a boss part (7) that radially protrudes from the outer peripheral s...  
WO/2017/129908A1
The invention relates to an element (201) for injecting a mixture of at least one first propellant (E1) and one second propellant (E2) into a combustion chamber. The injection element (201) includes a first tubular wall (202) defining a ...  
WO/2017/130134A1
The present invention relates to a process for the production of fiber- reinforced composite materials with an ultra-refractory, high tenacity, high ablation resistant matrix with self-healing properties, prepared from highly sinterable ...  
WO/2017/129894A1
The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X') of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) o...  
WO/2017/129661A1
The invention relates to a curable resin that represents an excellent substitute for phenolic resins and is therefore able to replace phenolic resins in all applications in which they are used. Said resin is characterised in that it comp...  
WO/2017/127629A1
A turbopump such as a liquid oxygen (LOX) turbopump for a liquid rocket engine is formed using a metal additive manufacturing process in which a single-piece impeller is formed within a single piece housing, the impeller being trapped wi...  
WO/2017/125663A1
The invention relates to an aircraft turbomachine fan module (1) comprising: a fan (2), a low pressure compressor (3), inlet guide vanes (18) located upstream of the low pressure compressor and downstream of the fan (2), and a device for...  
WO/2017/121115A1
A vector engine having a tail rudder. The present invention uses the principles of acting force and counter-acting force, fluid mechanics and Bernoulli's principle to design a tail rudder disposed at a tail end of a central shaft of a co...  
WO/2017/121114A1
A vector engine having rudders. A horizontal rudder (3) and a vertical rudder (7) processed with a heat-resistant material having a high technical specification are installed at a jet nozzle (2) of a jet engine. By adjusting angles of co...  
WO/2017/118820A1
The invention relates to a fan (2) of a turbine engine (1), said fan (2) including: a disc provided with blades (22) at the periphery thereof, said blades (22) being mounted so as to pivot on the disc about a pivot axis (Y); and a mechan...  
WO/2017/118793A1
The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor (2) carrying blades (3), a stationary housing (7), a mechanism (11, 12, 13, 14, 20) for regulating the pitch of the blades (3), which...  
WO/2017/118794A1
The invention relates to a streamlined fan module with variable-pitch blades for a turbine engine, including a rotor (2) supporting blades (3), a stationary housing (7) and a system (3) for adjusting and controlling the setting of the bl...  
WO/2017/118792A1
The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor ...  
WO/2017/109330A1
The present invention relates to a multiflow turbojet engine comprising: a. an upstream fan (2) driven by a gas generator; b. the gas generator comprising first (3) and second (4) coaxial compressors; c. an intake case (8) forming a moun...  
WO/2017/109374A1
The invention relates to a turbomachine comprising an inter-flow compartment (110) extending radially between first and second intermediate walls, gas bypass ducts (102) passing through the second intermediate wall and communicating with...  
WO/2017/109328A1
The present invention relates to a multi-flow turbojet engine comprising a. an upstream fan (2) driven by a gas generator, b. the gas generator comprising a first (3) and a second (4) compressor, which are coaxial, c. an inlet casing (8)...  
WO/2017/109430A1
The invention relates to a turbomachine (1) comprising at least two contra-rotating unducted propellers (10, 11) having blades (20, 21) extending radially, including an upstream propeller (10) and a downstream propeller (11), and a gas g...  
WO/2017/103503A1
A nacelle (1) comprising an exhaust nozzle (5) comprising at least one flap (8) pivoting between a retracted position and a deployed position, characterised in that the flap (8) is arranged downstream from an injection zone (9) where a c...  
WO/2017/103389A1
The invention relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle, comprising devices for actuating and controlling the reverser, including hydraulic locks and cylinders, the corresponding hydrauli...  
WO/2017/103464A1
The present invention relates to a nacelle for an aircraft turbojet engine, which comprises: a thrust reverser comprising: a cowl movable between an extended position and a retracted position, and a stationary structure; a secondary nozz...  
WO/2017/097665A1
The invention relates to an aircraft gas turbine, comprising a core engine (10) and a bypass flow channel (25), which bypasses the core engine and which forms an outlet nozzle (31) together with a casing (29) of the core engine (10) and ...  
WO/2017/085406A1
The invention relates to a propulsion unit (2) configured to provide takeoff thrust and top of climb thrust and comprising: - a main engine (3), configured to supply main thrust during the takeoff phase and during the top of climb phase ...  
WO/2017/085386A1
The invention relates to a front part of an aircraft turbomachine (1) of the bypass type comprising a single fan (15), a gas generator (2) positioned downstream of the fan (15), a reducer (20) interposed between the gas generator (2) and...  
WO/2017/082968A1
A motor assembly (10) is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle (42) and a casing disposed about the aerospike nozzle, where inter...  
WO/2017/077219A1
The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube and the cone comprise centring means engaging together. The invention also relates to a locating and ad...  
WO/2017/077873A1
An injection device, a combustor and a rocket engine which are provided with an injection device body (21) that demarcates an oxidizer manifold (33) and a fuel manifold (34), and also provided with a plurality of injectors (22, 23, 24) t...  
WO/2017/078931A1
A rocket motor includes a case and first and second nozzles in the case. The first nozzle is disposed in the second nozzle. The first nozzle includes a forward leg, a rear leg, and an intermediate leg. The intermediate leg has a convex c...  
WO/2017/075718A1
An air breathing jet engine for a supersonic or hypersonic vehicle has an air passage having an air inlet, an air outlet, and a combustion chamber between the air inlet and the air outlet; one or more nozzles positioned in the air passag...  
WO/2017/075717A1
There is provided a hypersonic air-breathing engine having an air passage with an inlet, an outlet, and an air flow, and a turbojet between the inlet and the outlet. There is an air bypass around the turbojet, an afterburner downstream o...  
WO/2017/077874A1
A combustor and rocket engine which are equipped with: an injection device (11) for injecting fuel and an oxidizer from an injection surface (23); a combustion chamber (12) for generating a combustion gas by combusting the fuel and the o...  
WO/2017/078821A3
An exhaust cooling arrangement includes a first duct having a first inlet and a first outlet, a fairing positioned radially outwardly of the first duct defining an annular space between the fairing and the first duct, and a second duct h...  
WO/2017/072458A1
An extrusion device (100) intended for the manufacture of a continuous strip (50) of a profiled product made of elastomeric material comprises a fixed body (110) containing at least one rotationally driven screw (120), a feed hopper (130...  
WO/2017/074345A1
An improved combustion system in a combustion turbine engine is provided. The combustor system may include an injector assembly (12) disposed in a combustion stage disposed downstream from a main combustion stage of the combustor system....  
WO/2017/074222A1
The invention relates to the field of engine building, and more particularly to jet nozzles with noise reduction devices, and is intended for use in aircraft engines. A chevron nozzle of a gas turbine engine comprises an exhaust pipe (2)...  

Matches 1 - 50 out of 9,065