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Matches 1 - 50 out of 8,880

Document Document Title
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/2017/064422A1
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/2017/061433A1
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 ...  
WO/2017/044081A1
A thrust reverser assembly for high-bypass turbofan engine. The thrust reverser assembly includes a translating cowl mounted to a nacelle of an engine. The thrust reverser assembly includes blocker doors axially guided adjacent first end...  
WO/2017/040160A1
A rocket motor (20) includes a nozzle (22) and a solid propellant section (24) in communication with the nozzle. The solid propellant section includes a first energetic grain layer (38, 32) that has a top surface and a bottom surface, an...  
WO/2017/041018A1
A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore condu...  
WO/2017/039941A1
A solid rocket motor includes a case, a solid propellant, and a seal attached to the motor. The seal isolates the solid propellant from a fluid external of the case, and the seal is at least partially transparent.  
WO/2017/037378A1
The invention relates to a propulsion assembly, including a turbine engine configured to be attached to an aircraft by means of a suspension, of which some housing portions may be uncoupled to attenuate some bending modes of the turbine ...  
WO/2017/037399A1
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...  
WO/2017/039783A3
A method for fabricating a solid rocket motor case (26) includes applying an insulator material (34) around a mandrel, embedding at least two rigid support pieces (36) in the insulator material (34), wherein the at least two rigid suppor...  
WO/2017/031512A1
The invention relates to an actuating mechanism (1) for adjusting at least one module (11) of a spacecraft, comprising a connecting plate (2) for connection to the module (11) and a cardanic suspension having two axes of rotation (3,4) f...  
WO/2017/027198A1
A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.  
WO/2017/027217A1
A solid rocket motor includes a propellant grain and a barrier shielding at least a portion of the grain. The barrier is impermeable to water, oxygen, nitrogen, and volatile solid propellant species.  
WO/2017/021651A1
The invention relates to a method and device for controlling the pressure (PGC) and a mixture ratio of a rocket engine on the basis of a set pressure value (PGCc) and set mixture ratio value (RMc). In said method and device, a control ge...  
WO/2017/021628A1
The invention particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft, comprising an acoustically reflective wall and a sandwich panel, the sandwich panel comprising a honeycomb structure surrou...  
WO/2017/023383A1
In one aspect and one example, a liquid fueled pulsed plasma thruster includes an ionic liquid propellant and electrodes disposed to at least partially cause electrolytic decomposition of the ionic liquid propellant. The ionic liquid pro...  
WO/2017/016710A1
The invention relates to an engine (10) for an aircraft (12) and to an aircraft (12) or winged aircraft (12) having an engine (10), wherein the engine (10) comprises a fan (14) and a compressor (16), wherein impellers (20) of the fan (14...  
WO/2017/017024A1
A charge gas compression train (1) for ethylene,comprising on the same shaft line a steam turbine (2) and a first compressor (60) comprising a first group of compression stages(3), a second group of compression stages(4) and a third grou...  
WO/2017/017369A1
The invention relates to a method for producing an acoustic attenuation panel comprising two outer skins (4, 6) made from a composite material with a ceramic matrix containing a fibrous reinforcement, said skins being assembled on each s...  
WO/2017/017392A1
The proposed invention is an air-flow straightening assembly for a turbine engine comprising: - a cylindrical platform (15) centred on an axis (X-X), - at least one straightener blade (20) extending from the platform, - a structural arm ...  
WO/2017/017378A1
The invention concerns an anti-icing system for a turbine engine blade (A1) extending between an outer housing (CE) and an inner housing (CI) delimiting a flow path (VN), characterised in that it comprises means for injecting a jet of ai...  
WO/2017/017367A1
The invention relates to a method for producing an acoustic attenuation panel from a composite material with a ceramic oxide matrix, comprising the following steps: a) draping a plurality of plies in a mould, said plies consisting of fib...  
WO/2017/013360A1
The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two...  
WO/2017/013366A1
The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power tur...  

Matches 1 - 50 out of 8,880