Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 8,931

Document Document Title
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)...  
WO/2017/074224A1
The invention relates to engine design, and more particularly to thrust reversers for gas turbine engines. The present device for connecting a thrust reverser to the front housing of an engine comprises a wedge lock with a circumferentia...  
WO/2017/067774A1
The present invention relates to a flow engine (10) comprising an outlet arrangement (12) with a diffuser arrangement (14) comprising a diffuser section (16) and with an exhaust arrangement (18) comprising a cone section (20) and a colle...  
WO/2017/065859A3
A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the co...  
WO/2017/064422A1
The present invention relates to a variable cross-section nozzle (13) for an aircraft nacelle (1) having a longitudinal axis (X), the nozzle (13) comprising doors (P) movable between a smaller cross-section position and a larger cross-se...  
WO/2017/065858A3
A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly d...  
WO/2017/061433A1
Provided are a casing for a gas turbine and a gas turbine. The present invention comprises: a first casing (31) that is provided with a first flange section (42), a plurality of first connection holes (43), and a plurality of first cutaw...  
WO/2017/060584A1
The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least o...  
WO/2017/062335A1
A flex joint (22) includes a bellows (33) and a liner system (46) disposed in the bellows. The liner system includes two generally cylindrical liner pieces (50,52) that are connected to each other in an articulated joint (54). One of the...  
WO/2017/062408A1
Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body ...  
WO/2017/062077A1
A gas generation system for generating gases, such as for use as or as part of a rocket motor in propelling a projectile, includes two or more propellant charges and electrically operated propellant initiators operatively coupled to resp...  
WO/2017/048041A1
The present invention relates to a liquid rocket engine using a booster pump driven by an electric motor and, more specifically, to a liquid rocket engine using a booster pump driven by an electric motor, the liquid rocket engine having ...  
WO/2017/046788A1
An aircraft engine system configured with a high pressure stage turbocharger assembly and a supplemental stage turbocharger assembly disposed in series with respect to said high pressure stage turbocharger, wherein the supplemental stage...  
WO/2017/046481A1
The invention relates to a bowl (35) intended to supply oil to at least two oil-distribution circuits (43-44, 45-45a-45b) which are connected to a planet carrier (13) of an epicyclic reduction gearbox (10), the said planet carrier (13) r...  
WO/2017/048039A1
The present invention relates to a liquid rocket engine using a pump driven by an electric motor and, more specifically, to a liquid rocket engine using a pump driven by an electric motor, the liquid rocket engine enabling the system to ...  

Matches 1 - 50 out of 8,931