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Matches 1 - 50 out of 9,457

Document Document Title
WO/2019/050511A1
An internal combustion engine with a piston having a piston head with a resonance cavity opening onto the head, and where a fuel nozzle located in a cylinder head is positioned to inject a fuel such as natural gas into the combustion cha...  
WO/2019/045997A1
A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rota...  
WO/2019/045669A1
A pulsed compressive detonation device comprises a piston compressor (1) consisting of at least a cylinder (2) that houses a piston (3) provided with a reciprocating motion actuator (4), an intake manifold (6) connected to the cylinder (...  
WO/2019/043343A1
The invention relates to a thrust reverser for a turbojet engine nacelle, comprising thrust reversal cascade vanes (10) arranged about an annular flow duct comprising a stationary front casing (2); at least one movable cover (4) moving b...  
WO/2019/043326A1
Disclosed is a method for managing the thrust of a rocket engine (100) by which an initial thrust setpoint (PGCc ini) is computed. Taking into account at least one limitation of the electrical power supply (104), a filtered thrust setpoi...  
WO/2019/043342A1
The invention relates to a sealing device (6) for an aircraft turbojet engine nacelle, comprising a seal (61) provided with a tubular part (611), a support element (62) accepting this seal (61) in a sealing position, and an attachment sy...  
WO/2019/038510A1
The invention relates to a twin-spool turbojet engine (1) comprising: – a low-pressure spool (3), comprising a low-pressure compressor (31), a low-pressure turbine (32) and a low-pressure shaft (33) connecting the low-pressure turbine ...  
WO/2019/038501A1
A supply system (1) for supplying a rocket engine with at least one propellant, the supply system (1) comprising at least one supply circuit (10) able to circulate the propellant and at least one tank (20) in fluid communication with the...  
WO/2019/038503A1
An assembly for the rear of a bypass turbomachine (10) comprises a primary nozzle (11) comprising a trailing edge defining a primary flow path portion and a secondary nozzle (110) defining a secondary flow path portion, defined about a l...  
WO/2019/038505A1
A panel (3) for a nacelle of an aircraft propulsion assembly, comprising two skins (31, 32) and a cell structure provided with transverse partitions defining cells (344, 345). The cell structure comprises folds (35) each comprising at le...  
WO/2019/037816A1
The invention relates to a jet engine, which has a stationary housing, in which housing a primary flow is formed, in which inflowing air is burned in at least one combustion chamber, and in which housing a secondary flow is formed, in wh...  
WO/2019/036053A1
A system that includes a turbofan engine, a nacelle surrounding the engine and defining an annular bypass duct through the engine to define a generally forward-to-aft bypass air flow path, a thrust reverser movable to and from a reversin...  
WO/2019/034851A1
The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one pla...  
WO/2019/030462A1
A method for manufacturing a fibrous tubular structure (11) comprising lobes (9), in which fibres (13, 15) are draped/deposited on a mandrel (19) having a shape corresponding to that of this fibrous structure (11), this draping/depositio...  
WO/2019/030454A1
The invention relates to a thrust reverser cascade (1) for an aircraft nacelle, comprising a plurality of blades (2) having a first (6a) and a second surface (6b), the blades (2) being connected to members (3, 4) connected to attachment ...  
WO/2019/021234A1
A space propulsion system (1), having reduced sizes, is designed specifically for the application on miniaturised satellites, but it can be scaled easily based upon a wide range of sizes of the target vehicle, and it comprises: a combust...  
WO/2019/020995A1
A nacelle for an aircraft having a thrust reverser including a translating cowl and a blocking panel. The blocking panel is connected by a pivot connection and is connected to the translating cowl by a sliding connection including an eng...  
WO/2019/020951A1
Method for detecting ignition in a combustion chamber (10) of a rocket motor, in which : A) for each of the propellants (H,O), values are acquired for parameters that make it possible to calculate the mean values PGC_H0, PGC_H1 and the s...  
WO/2019/014386A1
A system for enhancing the thrust produced by an aircraft propulsion element having a propulsion fluid outlet includes a shroud element having an inlet, an outlet and a diffusing section positioned between the shroud element inlet and sh...  
WO/2019/009235A1
This combustion chamber cooling mechanism is provided with: a bottom wall in contact with a combustion chamber; an upper wall disposed on the opposite side of the combustion chamber from the bottom wall; and a plurality of sidewalls whic...  
WO/2019/005937A1
A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and re...  
WO/2019/002753A1
The invention relates to a nacelle for a turbojet comprising a thrust reverser comprising cascades (14), movable cowls adjacent to these cascades (14) in a closed position, connection systems for connecting the cowls and the cascades (14...  
WO/2019/000932A1
An inter-stage segment structure for a carrier and a carrier. The inter-stage segment structure for a carrier comprises an annular skin (1). A first edge of the skin (1) is provided with a lower end frame (6); a middle frame (8) is provi...  
WO/2018/234766A1
A rocket motor for a vertical take-off and landing (VTOL) aircraft is provided, along with control circuitry and computer programs for controlling the rocket motor, the methods of using the rocket motor. The rocket motor may define an el...  
WO/2018/229317A4
A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape...  
WO/2018/229421A1
The invention relates to a turbopump for a spacecraft, comprising: an intake pipe (1) opening into an intake cavity (2) defined by an inner wall; an impeller; an induction pipe (3) extending from the intake cavity (2); and an inducer (4)...  
WO/2018/227317A1
A super large and a large rocket thrust chamber for human lunar exploration or Mars exploration. The thrust chamber may contain liquid oxygen/kerosene, liquid oxygen/liquid hydrogen, hydrogen peroxide/NHMF or kerosene or liquid hydrogen,...  
WO/2018/231800A1
Propulsion systems that generate thrust from pressure generated by thermally decomposing a chemical blowing agent (CBA). In some embodiments, the CBA decomposes exothermically such that once thermal decomposition has been initiated, the ...  
WO/2018/229317A1
A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape...  
WO/2018/226268A1
A flight vehicle has an engine that includes air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes a bulged region that has at least one dimension, perpendicul...  
WO/2018/226269A1
A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an ...  
WO/2018/224809A1
A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured...  
WO/2018/224998A1
An attitude control and thrust boosting system (100) for a space launcher is disclosed, wherein the space launcher is equipped with a rocket engine (303) provided with an exhaust nozzle. The exhaust nozzle comprises a divergent portion (...  
WO/2018/219856A1
The invention relates to a method and a device for increasing the efficiency of jet propulsions by recuperating effective power from the propulsion flow. A ducted fan (4), driven by a drive motor (9) via a driveshaft (1) and located in t...  
WO/2018/221437A1
According to the present invention, a heat transfer body 3 having an inner space 7 in which a high temperature-side fluid is generated or flows is prepared. The heat transfer body 3 is a component of a heat exchanger, and is a wall forme...  
WO/2018/215717A1
The invention relates to a tubular structure (11) comprising lobes (9), characterised in that the structure is produced as a single piece over at least two lobes, in that the circumferential fibres (15) have a constant orientation with r...  
WO/2018/216255A1
[Problem] To provide a blade for fan and compressor having an enlarged laminar flow region on the blade surface and reduced loss. [Solution] A blade of the present disclosure is divided into a subsonic region where the relative Mach numb...  
WO/2018/217264A1
A multi-stage solid rocket in accordance with this disclosure includes a first or primary solid fuel core that operates as a standard solid rocket. A secondary solid fuel core may be "wrapped around" the primary solid fuel core in a laye...  
WO/2018/203153A1
An engine that uses detonation for generating energy includes a housing (300); an inlet (306) configured to inject a fuel mixture (304) into an ignition region (320) of the housing (300), the inlet being attached to the housing (300); an...  
WO/2018/202962A1
A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary strea...  
WO/2018/202738A1
These new thrusters simultaneously use wheels of the CARPYZ THRA "Turbo Powered Helicopter Reactor" type and wheels of the CARPYZ TaG ''Bucket Turbines'' type or wheels of the CARPYZ TaC ''Scoop Turbines" type, representing real global t...  
WO/2018/197232A1
The invention relates to an aircraft propulsion assembly (10), comprising a turbine engine surrounded by a nacelle (26) comprising an annular air-intake lip (30) extending around the turbine engine by two annular walls, inner (34) and ou...  
WO/2018/193217A1
The present invention relates to: - copolymers made up of butadiene units (B), vinyltetrazole units (VT), acrylonitrile units (AN) and R-terminal groups that are not able to react with azide functions; in which the vinyltetrazole units (...  
WO/2018/195122A1
This disclosure relates to various seals for sealing around exhaust pipes, such as the exhaust pipe of an aircraft auxiliary power unit. The seal can include a collar portion bounding an opening that is configured to receive the exhaust ...  
WO/2018/189944A1
A regenerative cooler (2) is provided with a flow passage forming structure (10) having formed therein a fuel flow passage (11) to which liquid fuel is supplied. A coating (12, 12A) at least partially covering a wall surface of the fuel ...  
WO/2018/185961A1
This pump for rocket fuel, which is provided with a rotating body (4) mounted on a rotating shaft (3), and in which the rotating body (4) is rotated by a drive source (T) to feed the rocket fuel, is provided with a magnetic coupling (R) ...  
WO/2018/186927A1
Systems and methods for adjusting an operating parameter of a machine based on an operating state of a component of the machine are provided. A method may be implemented by an electronic control unit (ECU) of the machine and includes det...  
WO/2018/183401A1
An apparatus and method of operating a translating cowl for a turbine engine. The translating cowl is moveable between a first position and a second position. The translating cowl includes a fixed cascade element located within and a blo...  
WO/2018/175037A1
Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical i...  
WO/2018/174943A1
An air inlet for a flight vehicle engine includes at least one fin, at least partially upstream of a throat of the engine. The fin protrudes into a flow channel, extending beyond a boundary layer into the main airstream in the inlet. The...  

Matches 1 - 50 out of 9,457