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Matches 1 - 50 out of 8,813

Document Document Title
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 ...  
WO/2017/011208A1
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 ...  
WO/2016/181307A1
The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which...  
WO/2016/182496A1
The present invention relates to an ignition system for a liquid propellant chemical rocket engine, which comprises a thermal-catalytic element (20) for initiating decomposition of the liquid propellant, and an electrical heater (30) for...  
WO/2016/174330A1
The invention relates to a torque meter comprising a casing (12) in which a translationally movable part (14) may move in a longitudinal direction under the effect of an axial pressure representative of the torque to be measured. The tor...  
WO/2016/167700A1
The present invention relates to a liquid propellant chemical rocket engine reactor Thermal Management System (TMS), which system comprises a reactor comprising a thermally conductive reactor housing, a heat bed, and a catalyst bed, whic...  
WO/2016/157224A1
Described is a propulsion system (1) for hypersonic aircraft, having an air inlet (10) of a fluid (110), a containment duct (20) and an exhaust nozzle (30). The propulsion system (1) comprises a bypass duct (40) for a flow (100) of fluid...  
WO/2016/156739A1
The invention relates to a hub (2) of an intermediate casing (1) for a dual-flow turbine engine, said hub (2) comprising: a discharge flow duct (18) extending between an inner shroud (3) and an outer shroud (5) of the hub (2), the discha...  
WO/2016/156935A1
The present disclosure relates to a dismantleable mandrel assembly and a method of molding solid propellant grains with deep fin cavities whose major transverse dimensions are larger than casing opening dimensions in a monolithic rocket ...  
WO/2016/153577A2
An aircraft, launch vehicle, or spacecraft propulsion device called DiscThrusterTM which creates thrust in the form of pressure thrust, as opposed to momentum thrust, wherein a thin round DiscThruster disc 2 spins about its disc rotation...  
WO/2016/151267A1
The invention relates to a device for reducing the jet noise of a turbine engine, comprising an outer cowl (16) provided inside a wall (20) defining on the outside an annular section (22) for the flow of a secondary stream from the turbi...  
WO/2016/151236A1
The invention relates to an aircraft turbine engine, comprising a low-pressure body including a low-pressure shaft (24), means (44) for collecting power on said low-pressure shaft, and a fan (28) driven by said low-pressure shaft via a r...  
WO/2016/151609A1
Described is an air plasma propulsion system comprising: a plant (100) with an air turbine (A) designed to receive a supply of air (A) from an outside environment, and a plasma propulsion unit (200) designed to increase a speed of the ai...  

Matches 1 - 50 out of 8,813