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Matches 651 - 700 out of 9,922

Document Document Title
WO/2015/193499A1
The present invention relates to a method (50) for controlling the orbit of a satellite (10) in earth orbit, the orbit of the satellite (10) being controlled by commanding, according to a plane of operation, the propulsion means (30, 31)...  
WO/2015/189524A1
The invention relates to a lubrication device for a turbine engine, comprising an oil intake pipe (23) provided with a pump (24) for supplying oil and control means (25) located downstream from the supply pump (24), a supply pipe (26) in...  
WO/2015/188143A1
Solid materials may be processed using shockwaves produced in a supersonic gaseous vortex. A high]velocity stream of gas may be introduced into a reactor. The reactor may have a chamber, a solid material inlet, a gas inlet, and an outlet...  
WO/2015/185312A1
The invention relates to a method for the combustion of an electropositive metal using a combustion gas, which electropositive metal is drawn, in the form of a fluid or powder having particles with a particle size of less than 100 ┬Ám, o...  
WO/2015/181512A1
This new ramjet consists of an air intake port (11), a diffuser stage (12), a fuel source (13), a combustion stage (14), and an exhaust nozzle (15). There are impellors in the diffuser stage that draw air into the engine when the aircraf...  
WO/2015/181471A1
The present invention relates to a turbo engine nacelle, comprising an external cowling (3) having an internal wall defining, with an internal fixed structure, an annular flow channel (15) for a secondary airflow, and an exhaust nozzle (...  
WO/2015/176190A1
The invention relates to a device serving for repeated production of explosions. The device comprises: an explosion chamber (11), a feed line for feeding a free-flowing explosive material, a vent opening for directed venting of a gas pre...  
WO/2015/177438A1
An engine (10) for a spacecraft comprising a chemical thruster comprising a nozzle (30) for ejecting combustion gas, and a Hall-effect thruster. The engine is arranged such that the nozzle acts as an ejection channel for particles ejecte...  
WO/2015/177467A1
The invention relates to a device for controlling a flow of a gas in a pipe (1), including a valve (2) provided with an actuator (3), the valve (2) being configured such as to selectively seal the pipe (1), characterised in that the move...  
WO/2015/178477A1
A thrust increasing device (10) comprises: a fuel injector (10b) that injects fuel into a jet flow; an ignition device (10c) that is disposed downstream of the fuel injector; a cylindrical duct (10a) that surrounds a combustion region; a...  
WO/2015/142395A3
The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.  
WO/2015/171411A1
A fragmenting nozzle system includes a first nozzle at least partially disposed within a second nozzle. The first nozzle includes an ablative shell, a syntactic foam support disposed between the ablative shell and the second nozzle, and ...  
WO/2015/112231A3
A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flo...  
WO/2015/166430A1
Aircraft (10) of the type comprising: - a fuselage (11); - a main wing (12), a front tab (13) and a horizontal tail plane (15) so as to make three lifting surfaces; - two turboprop units (34) mounted on the main wing (12) on opposite par...  
WO/2015/130386A3
The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a ro...  
WO/2015/166831A1
Provided are: a heat-resistant metal member which has excellent heat resistance and durability and is capable of greatly improving high-temperature corrosion resistance of a metal base that is formed of Nb, an Nb-Hf-based alloy or an Nb-...  
WO/2015/130382A3
A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path ...  
WO/2015/166178A1
The invention relates to an assembly (100) for an aircraft turbine engine, comprising: a rolling bearing bracket (70) defining an inner space (78) on either side thereof; a rotary assembly (58, 60, 38) comprising a first gear (38); a hou...  
WO/2015/166902A1
The present invention sufficiently ensures the ignition stability and the flame-holding property of an afterburner (25) while suppressing a reduction in the engine efficiency of an aircraft engine (1). A flame holder (45) is disposed dir...  
WO/2015/166179A1
The invention relates to an aircraft turbine engine (1) comprising a fan (15) as well as a reduction gear (20) including a plurality of rotary elements (52, 58) and driving the fan, the turbine engine also including a gearbox (32) as wel...  
WO/2015/130384A3
The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an ...  
WO/2015/166187A1
The invention relates to a modular assembly for a turbine engine, comprising an annular bearing support (26) including means for connecting to a first anti-friction bearing (24) designed to be mounted around a first shaft (16) of the tur...  
WO/2015/166921A1
The present invention improves the durability of an afterburner (25) and yet suppresses a reduction in the engine efficiency of an aircraft engine (1). A ring-shaped cooling channel (35) through which cooling air (CA) flows is formed bet...  
WO/2014/133911A3
Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed rela...  
WO/2015/159944A1
A vapor jet system which includes: a container which accommodates a sublimable solid and is equipped with a vapor discharge port for discharging vapor generated by sublimation of the sublimable solid; a member which is equipped with an o...  
WO/2015/116283A3
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pres...  
WO/2015/156872A2
An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using th...  
WO/2015/155733A1
A combustor (2) for a liquid propellent motor (1) has an elongated hollow tubular casing (4) having an inner wall (12) delimiting a combustion chamber (8) for the liquid propellent and an outlet nozzle (11) for the combustion products, a...  
WO/2015/155432A1
The present invention relates to a door-type thrust reverser device (21) for a turbojet engine nacelle, comprising: - a fixed structure (31), and - a mobile structure (33) mobile with respect to said fixed structure, comprising at least ...  
WO/2015/155434A1
The invention relates to a thrust reverser of a turbofan pod, comprising movable cowlings (4) that retract relative to stationary front structure (2) to reveal stationary or movable thrust reverser cascades, as well as a secondary variab...  
WO/2015/150707A1
The invention relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a transverse pivot in order to partially close off the ...  
WO/2015/150706A1
The method according to the invention includes: a step (E10) of obtaining a measurement of the monitored parameter carried out by a sensor and corresponding to an operating point of the engine, said operating point being defined by at le...  
WO/2015/151621A1
This jet engine is provided with an inlet that takes in air, a combustor (12) that combusts a fuel using air, and a fuel control unit (37) that controls the supply of fuel. The combustor (12) is provided with a fuel supply unit (22) that...  
WO/2015/151062A1
A solid propellant rocket motor (1) has a tubular casing (3) accommodating a mass (5) of solid propellant material and at least one opening (10) for the space in the casing (3) to communicate with the outside closed by a closing head (11...  
WO/2015/151620A1
This jet engine is provided with an inlet and a combustor. The inlet (11) takes in air. The combustor combusts a fuel using air. The combustor is provided with an injector (20). The injector (20) has an opening portion (31) for injecting...  
WO/2015/150653A1
Bypass turbojet engine nacelle thrust reverser comprising mobile cowls (4) which retract with respect to a fixed forward structure (2) in order to uncover thrust reversal cascades or vanes, and a variable secondary nozzle (6) connected t...  
WO/2015/146357A1
A combustor (7) of this jet engine comprises: a fuel injector (62); an igniter (61) for igniting a gas mixture of air and a fuel; and a flame-holding part (66, 66'). The igniter (61) is arranged within the flame-holding part (66, 66'). A...  
WO/2015/145041A1
The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4...  
WO/2015/146375A1
This jet engine comprises: an inlet (11) that takes in air; and a combustor (12) that combusts a fuel by using said air. The combustor (12) includes an injector (20), a plurality of flame holders (21, 22), and a disappearing part (31). T...  
WO/2015/146376A1
This jet engine comprises an inlet and a combustor. The inlet takes in air. The combustor combusts a fuel by using said air. The combustor (12) includes an injector (20) that is provided with a plurality of openings (31a, 31b) for inject...  
WO/2015/145056A1
The invention relates to a thrust reversal device (12) for an aircraft turbojet engine pod including at least one movable cover (22) and a thrust reversal flap (26) that extends from a head (28) to a leg (30). Said device is characterize...  
WO/2015/146356A1
This jet engine comprises: an inlet (6) that takes in air; and a combustor (7) that combusts a fuel by using said air. The combustor (7) includes a fuel injector (62), and an igniter (61) for igniting a gas mixture of said air and said f...  
WO/2015/140450A1
The invention relates to a locking device (12) for a thrust reverser (14) with door (16) equipping a turbo jet engine nacelle (10), characterized in that the device (12) comprises a first fitting (28) secured to the door (16) and a secon...  
WO/2015/142395A2
The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.  
WO/2015/142394A1
A hybrid structure comprises a metallic built-up sandwich structure, and a monolithic superplastic formed and diffusion bonded structure joined to the built-up sandwich structure.  
WO/2015/143362A1
In one embodiment, a power generation system includes a pulse detonation engine including a combustion chamber, a linear power generator including a working chamber, and a nozzle positioned between the combustion chamber and the working ...  
WO/2015/138033A1
An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second z...  
WO/2015/134081A2
The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator...  
WO/2015/133639A1
A blade for a propeller constituting an aircraft engine that constitutes a reaction engine or composite reaction engine configured such that, in order to produce a sustained output at the theoretical rotational speed of an axial compress...  
WO/2015/130386A2
The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a ro...  

Matches 651 - 700 out of 9,922