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Matches 1 - 50 out of 8,848

Document Document Title
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/2017/031512A1
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...  
WO/2017/013341A1
A device for modifying a gas ejection section (130) intended to be placed in a nozzle (120) upstream of the throat (121) of said nozzle comprises a needle (140). The needle (140) comprises a proximal part (142) connected to a control gui...  
WO/2017/013077A1
The invention relates to a drive device for an aircraft, comprising a shaft turbine coupled to an impeller by means of a shaft. The impeller comprises a suction side and a thrust side. The shaft turbine is arranged in the region of the s...  
WO/2017/013361A1
The invention relates to an aircraft comprising a fuselage (1) and a propulsion assembly, said propulsion assembly comprising at least one fan rotor (7, 8) located at the rear of the fuselage (1) in the extension thereof along a longitud...  
WO/2017/013365A1
The invention concerns an aircraft comprising a fuselage (1) and propelled by a turbine engine having two coaxial and contrarotating fans (7, 8), the turbine engine comprising a power turbine (3) having two contrarotating rotors, one of ...  
WO/2017/013364A1
The invention relates to an aircraft including a fuselage (1) and a propulsion assembly. Said propulsion assembly includes at least one fan rotor (7, 8) placed behind the fuselage (1) as an extension thereof along a longitudinal axis (XX...  
WO/2017/013362A1
The invention relates to an aircraft propulsion assembly, including a turbine engine comprising at least one gas generator (2a, 2b) configured to generate a main flow, which is supplied by a central jet (4) to at least one power turbine ...  
WO2017011208A1
A flow control system (22) includes a fuel passage network (34) that has first (36) and second (38) network portions that are in a parallel flow arrangement with each other. A fueldraulic device (40) is located in the first network porti...  
WO2016200460A3
A pulse combustor system for operating pulse combustors in anti-phase. The pulse combustor system includes two pulse combustors connected at their combustion chambers by a connecting tube. Each of the pulse combustors has a fundamental o...  
WO/2017/002481A1
A laser propulsion device (1) is equipped with a main body part (2), which stores a propellant (P) and is equipped with an aperture part (21) forming an irradiation surface for laser light (L), and a laser irradiation device (3), which e...  
WO/2017/003447A1
A catalytic thruster includes a reaction chamber that extends between first and second opposed chamber ends. The first chamber end includes a thermal standoff cup. There is a catalyst bed in the reaction chamber, and a feed tube extends ...  
WO/2016/207535A1
The invention relates to a rocket motor igniter (10), characterized in that it includes a spark plug (12), movable between a stowed position and a deployed position, and a pressure compensation chamber (14) having a first inner cavity (1...  
WO/2016/203157A1
The invention relates to a hub (2) of an intermediate casing (1) for a bypass turbomachine comprising: - a bleed stream duct (18), - a bleed valve, comprising a mobile door at the inlet orifice to the bleed stream duct (18), - a set of b...  
WO/2016/203138A1
System (100) for supplying an igniter with propellant, comprising - a reservoir (10) having an intake (11) and a discharge (12), - a liquid propellant supply line connected to the intake (11) of the reservoir (10), - a propellant dischar...  
WO/2016/203540A1
A structure for the rear part of a jet engine has an axis. The structure comprises: a casing surrounding a duct about the axis and open axially forward and rearward; a cone having a pointed rear end, the cone forming a first angle relati...  
WO/2016/200893A1
A track lock assembly (100) includes a pawl assembly (110) comprising a pawl arm (112) extending from a pawl axis (116) and configured to engage a slot (20) in a slider assembly (10), a cam arm (114) extending from the pawl axis (116) an...  
WO/2016/198806A1
The invention relates to an assembly comprising: - a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also inc...  
WO/2016/200698A1
An engine, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation/combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending fro...  
WO/2016/195761A1
A nozzleless hybrid rocket motor includes a fuel element that defines a combustion chamber therewithin, in which combustion of the fuel and an oxidizer occurs. The combustion gases produced by the combustion between the fuel and the oxid...  
WO/2016/193623A1
The invention relates to an aircraft turbine engine nacelle thrust reverser including: at least one translatable thrust reverser cowl, an output nozzle of variable cross-section, an actuator suitable for moving the variable nozzle and th...  
WO/2016/193890A1
An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (...  
WO/2016/195795A1
A non-destructive testing system (200B) for propellant for a rocket is provided. The system includes an insertion tube (210) having a first end and a second end in addition to a support sleeve (212) configured to mate with a casing (112)...  
WO/2016/195762A1
A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and t...  
WO/2016/189712A1
This jet engine (1) is provided with: a fan (3, 31, 32, 33) having moving blades (3b1, 3d1, 3g1, 3i1, 3k1) in a plurality of stages; compressors (4, 5) which compress air fed from the fan (3, 31, 32, 33); a combustor (6) which generates ...  
WO/2016/186566A1
The present invention relates to an electrical heater assembly (1) for liquid propellant chemical rocket engines, and more particularly to such heater assembly comprising a heating cable (30) and a heater support (10), wherein the heater...  
WO/2016/185119A1
The invention relates to an intermediate casing hub of an aircraft turbojet engine, which includes: an outer shroud (14) intended for defining a secondary flow space of a stream of secondary gas on the inside and an inter-flow area on th...  
WO/2016/181072A1
The invention relates to a lobed mixer (8) for arranging on the downstream end of a hood (4) separating the two coaxial streams, respectively inner and outer, the mixer (8) being shaped so as to have a least one peripheral succession of ...  

Matches 1 - 50 out of 8,848