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Matches 1 - 50 out of 9,628

Document Document Title
WO/2019/217839A1
A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle i...  
WO/2019/211518A1
The disclosure relates to a nozzle (12) for cooling a jet engine (2) for maintenance, wherein the jet engine (2) comprises an exhaust channel (21) for the exit of exhaust gases of the jet engine (2), the nozzle (12) comprises a suction a...  
WO/2019/211716A1
The subject of the invention is a ramjet-propelled projectile (1), the projectile comprising an outer body (2) and a deployable tail-fin assembly (3), the projectile comprising inside the body a chamber housing an abradable annular block...  
WO/2019/205787A1
A multi-redundancy electromechanical servo system for regulating a liquid rocket engine, comprising a triple-redundancy servo controller (1), a double-redundancy servo driver (2), double-winding electromechanical actuators (4, 5), a trip...  
WO/2019/204389A1
A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection ("EFI") system that further includes one or more electrically controlled fuel injectors that can be s...  
WO/2019/201969A1
The invention relates to a device for driving a generator (3) for generating electrical energy, said device comprising a rotor (10) that is rotatably mounted about an axis of rotation (5), wherein a plurality of rocket engines (14) havin...  
WO/2019/202269A1
The invention relates to a mixing tube (1) with multiple shapes allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachm...  
WO/2019/157477A9
A filtering apparatus formed by a plurality of channel systems. Each of the channel systems include an inlet port formed on an inlet side of the plate; no more than one outlet port formed on an outlet side of the plate; and a channel for...  
WO/2019/197144A1
The invention relates to an axial turbomachine, in particular a turbofan for an aircraft. The turbomachine comprising a compressor, also referred to as a booster, with a rotor (12) and a stator, a turbine, a combustion chamber axially be...  
WO/2019/197773A1
An acoustic treatment panel (10) to be arranged on at least one wall of a turbojet engine (1) in contact with a fluid stream, the panel (10) comprising a first acoustically reflecting plate (14), a second plate (16), and a plurality of c...  
WO/2019/191460A1
An aircraft includes an airframe, ducted fans, and ducts for carrying pressurized air for lift and thrust supplied by the fans. The ducts form part of the airframe and carry static and dynamic loads applied to the airframe. Ducting membe...  
WO/2019/179101A1
A vertical take-off and landing type throat-shifting aerodynamic vectoring nozzle based on a deflector, comprising: a fixing part disposed on the lower wall surface of a front expansion and convergence section of a second throat (9), and...  
WO/2019/180755A1
Automatic and continuous variation of the blade pitch without mechanical contact for applications in aeronautical turbofans. The actuation of the adjustable blade-holder supports with seat in the rotating hub of the fan takes place throu...  
WO/2019/179102A1
Disclosed is a short-distance take-off and landing throat offset-type pneumatic vector nozzle based on translational motion, comprising: tail sections of upper wall faces of front expansion and convergence sections of a second throat (8)...  
WO/2019/180360A1
Turbofan propulsion assembly comprising a thrust reverser with movable vanes. Said propulsion assembly comprises an engine (M) and a nacelle surrounding said engine, said nacelle itself comprising a thrust reverser with sliding vanes (15...  
WO/2019/175515A1
The invention concerns a system (1) for placing at least one satellite in working orbit, characterised in that the system (1) for placing in working orbit comprises: - a first attachment device (31) configured to attach a first satellite...  
WO/2019/176187A1
[Problem] To provide an injection device which uses a low-toxicity fuel agent and is compact, and of which life does not depend on catalyst life. [Solution] An injection device comprises a combustion vessel, a fuel supply source, and a l...  
WO/2019/178156A1
Rocket tank liquid level determination, and associated systems and methods. A representative system includes a computer-readable medium having instructions that, when executed, receive an image corresponding to a view of the liquid in th...  
WO/2019/174741A1
The present invention relates to a rocket engine for a rocket fuel having a working mass during the combustion of which a product with a dipole moment is produced. Said rocket engine comprises a combustion chamber, in particular having: ...  
WO/2019/171000A1
The invention relates to an active device for attenuating acoustic emissions (8) from a turbojet of an aircraft, characterised in that the device comprises conduits (20) for the circulation of a pressurised air flow supplying rotating el...  
WO/2019/172808A1
The invention relates to jet propulsors widely used, for example, in various transport vehicles and is intended for equipping transport vehicles moving in a three-dimensional liquid (for example, in water body) or gas (for example, in...  
WO/2019/167319A1
A turbo pump (1) is provided with: a main shaft (4) that is supported so as to be rotatable; a pump part (2) that is attached to one end of the main shaft (4) and that includes an impeller (8); and a turbine part (3) that includes a disk...  
WO/2019/163173A1
This rectifying structural body 100 of a flying object is provided with a rectifying part 30, a heat input control part 20, and a vacuum heat insulated part 10. The rectifying part 30 has a rectifying surface 30a and a rear surface 30b. ...  
WO/2019/162611A1
The invention relates to a drive unit comprising an engine such as a turbofan engine (4) and a nacelle which comprises, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers (8), a ...  
WO/2019/164557A1
A thrust reverser includes a frame having a longitudinal axis, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the first reverser door, a crank pivotally mounted to the frame, a first lin...  
WO/2019/162600A1
The invention relates to an aircraft turbine engine (10) comprising a primary air flow path (16) in which a low-pressure compressor (30) and a high-pressure compressor (32) are arranged, a secondary air flow path (20) comprising a plural...  
WO/2019/162610A1
The invention relates to a propulsion unit comprising a nacelle and a turbofan engine, comprising a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the tur...  
WO/2019/158884A1
The invention relates to a nacelle for a turbomachine, the nacelle comprising an inner wall that is annular about a longitudinal axis of the nacelle, the annular inner wall being designed to surround at least part of the turbomachine, th...  
WO/2019/158876A1
The invention relates to a profiled air flow structure comprising a body (62) and acoustically absorbent porous regions (52), having an upstream, a downstream, a leading edge (164) upstream and/or a profiled trailing edge downstream, and...  
WO/2019/158875A1
An aircraft turbine engine comprises an annular wall (160) for splitting a flow of air, downstream of an upstream fan (14), first stationary blades (24) for guiding a primary flow and the second stationary guidance blades (26) attached t...  
WO/2019/158854A1
The invention concerns an outer shroud (16) of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud comprising: - an annular downstream portion (24) provided with a shroud opening (30) passing through an annu...  
WO/2019/158867A1
The invention concerns a fire resistance device (50) intended to be interposed between an aircraft bypass turbine engine mounting structure (9) and a connection cowling (30) equipping this turbine engine, the connection cowling being int...  
WO/2019/155173A1
The hybrid propulsion is obtained by arranging, around a conventional turbomachine, a reversible electric machine (23) linked to the low-pressure shaft (7) via a mechanical movement transmission (25), a one-way clutch (29) being arranged...  
WO/2019/157477A1
A filtering apparatus formed by a plurality of channel systems. Each of the channel systems include an inlet port formed on an inlet side of the plate; no more than one outlet port formed on an outlet side of the plate; and a channel for...  
WO/2019/155015A1
A thrust reverser inner fixed structure comprising: a barrel portion; a discrete bifurcation; and a joint joining the discrete bifurcation to the barrel portion.  
WO/2019/155654A1
The purpose of the present invention is to improve the combustion efficiency of a scramjet engine. The scramjet engine is provided with a first and a second flow passageway forming members, and a first and a second fuel injection devices...  
WO/2019/155176A1
Method for detecting damage to one or more mobile blades of a bladed disc of an aircraft engine, comprising measuring (E1) the speed of the engine and, for each blade: – acquiring (E2) measurements of the blade-tip passage time, using ...  
WO/2019/149870A1
The invention relates to a combustion chamber device, comprising a combustion chamber (12), which is delimited by an inner jacket (14; 14'), wherein the inner jacket (14; 14') comprises a fluid-permeable structural material (32), and whe...  
WO/2019/141950A1
A rear assembly (18) of a nacelle (10) of a turbojet engine of an aircraft, the rear assembly (18) extending along a central longitudinal axis (A) and the rear assembly (18) comprising a sliding cascade (28) thrust reverser (2) that comp...  
WO/2019/141930A1
The invention relates to an optimized thrust reverser for an aircraft propulsion assembly in which the redirection of the air flow for performing the thrust reversal is effected by one or more membranes, i.e. by thin and flexible structu...  
WO/2019/136535A1
The present device for redirecting and lending momentum to streams of a fluid under pressure is positioned at the outlet of an external power device that generates propulsive thrust, such as a pump, a turbine, a propeller, or functional ...  
WO/2019/140029A1
The subject matter of this specification can be embodied in, among other things, a turbofan engine assembly includes a engine, a nacelle defining a generally forward-to-aft bypass air flow path, a thrust reverser comprising a first movab...  
WO/2019/135058A1
The invention relates to a structure (131) for the nacelle of an aircraft propulsion unit, comprising a first skin and stiffeners (3) arranged to hold acoustic treatment modules (4) against the first skin. Each acoustic treatment module ...  
WO/2019/129983A1
The invention relates to a method for producing a part made from a composite material, comprising the following steps: formation of a fibrous texture (10) using refractory ceramic fibres; placement of the fibrous texture (10) in a mould ...  
WO/2019/127936A1
Provided are a nozzle structure, a jet device and an engine. The nozzle structure (2) comprises: a nozzle body (10), the nozzle body (10) being provided with a liquid flow channel (11), with a first end of the liquid flow channel (11) be...  
WO/2019/129961A1
The invention concerns a grid-type thrust reverser (22) for a turbojet engine, the reverser comprising a moving O-shaped thrust reverser body (30) that is generally cylindrical in shape around a longitudinal central axis (A) and that com...  
WO/2019/121022A1
The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle comprising: a propelling nozzle wall (20), a duct (15), which is radially outwardly bounded by the propelling nozzle wall ...  
WO/2019/122657A1
A guide vane (15) in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis (Iz) of the vane (15) so that the differential thermal expansions compensate for the bending de...  
WO/2019/122753A1
The invention relates to a nacelle for a turbofan, comprising a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls (6, 8), said cascades moving rearwards with movab...  
WO/2019/122761A1
The present invention relates to a propulsion unit (5) for an aircraft, comprising: a nacelle (7), a turbojet engine (1), an annular passage (19) for a secondary air flow, and a pre-cooler device (3) in communication with an engine enclo...  

Matches 1 - 50 out of 9,628