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Matches 1 - 50 out of 8,766

Document Document Title
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...  
WO/2016/151251A1
The invention relates to the field of regulation of fluid flow rates, and in particular to a flow-rate-regulating device (109) comprising: an upstream chamber (206); a downstream chamber (207); a plurality of electrically conductive capi...  
WO/2016/146936A1
The invention concerns a thrust reverser (18) for an aircraft turbojet engine nacelle (10) comprising at least one movable thrust reverser cowling (20), a means for locking the cowling (20), an outlet nozzle (22) having a variable cross-...  
WO/2016/149075A1
A thruster nozzle (24) includes a throat (28) and a nozzle end portion (30) that is integral with the throat. The nozzle end portion includes an outer wall (32) that has a plurality of circumferentially-disposed nozzle features or connec...  
WO/2016/146939A1
The invention relates to a power package (1) comprising a gas turbine assembly (20) and a piston engine assembly (30), the power package (1) being characterised in that the piston engine assembly (30) is mechanically coupled to the gas t...  
WO/2016/144331A1
An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and...  
WO/2016/143827A1
The present invention is provided with a floor wall (22) that is in contact with a combustion chamber, an upper wall (30), and a cooling flow path (40) that is disposed between the floor wall (22) and the upper wall (30). The cooling flo...  
WO/2016/139417A1
An injector (1) of a propellant combustion member, comprising - a first supply (31) - a second supply (41), the first supply (31) being linked to a plurality of supply channels (33) disposed around a longitudinal axis (Z-Z), the second s...  
WO/2016/140866A1
A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also ...  
WO/2016/136635A1
An ignition system (10) is provided with: a fuel injection opening (30); a fuel reforming device (70); an ignition gas injection opening (50); and an ignition gas supply channel (52). The fuel injection opening (30) injects a hydrocarbon...  
WO/2016/138068A1
According to some embodiments, a system for widening and densifying a scrape-off layer (SOL) in a field reversed configuration (FRC) fusion reactor is disclosed. The system includes a gas box at one end of the reactor including a gas inl...  
WO/2016/132055A1
The invention relates to a constant-volume combustion system (3) for a turbine engine. Said system includes: - a plurality of combustion chambers (11-14) regularly distributed around a longitudinal axis (AX); - a toroidal manifold (7) in...  
WO/2016/133501A1
An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perfor...  
WO/2016/130120A1
A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls tha...  
WO/2016/128804A1
The present disclosure relates to propellant grain configuration in solid rocket motors. In one embodiment, the propellant grain is a case-bonded, forward- swept, deep finocyl grain offering significant flexibility in tailoring burn surf...  
WO/2016/128665A1
The invention relates to a turbine engine assembly comprising an air flow guide assembly, including at least one guide vane (21) and at least one structural arm (30), said vane and arm extending radially about an axis (X-X). The arm incl...  
WO/2016/128646A1
The invention relates to a flame-holder device (100) for the reheat channel of a turbojet comprising a chute-shaped arm (120) defining a cavity (121) and a heat shield (130) secured in the cavity of the arm. The flame-holder device (100)...  
WO/2016/128669A1
According to the invention, after a tank (18) is filled with liquid oxygen (20) to be used to supply a rocket engine (10) with fuel, but before the engine (10) is operated, the tank is pressurized by injecting gaseous nitrogen (N) therei...  
WO/2016/128664A1
The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line...  
WO/2016/126502A1
A power supply system and method for a vehicle movable within a structure is provided. The power supply system includes at least one energy source arranged at a fixed location within the structure to transmit energy within the structure,...  
WO/2016/120571A1
The invention relates to a system for correcting the pogo effect (5) for a system (3) for supplying a rocket engine (2) with liquid propellent, comprising: a portion of the duct (4A) for supplying liquid propellent configured to be conne...  
WO/2016/116711A1
The invention relates to a rear nacelle assembly (12) for a turbojet comprising at least one device (10) for thrust reversal by redirecting an air stream circulating from upstream to downstream in a channel of the turbojet, and a pylon d...  

Matches 1 - 50 out of 8,766