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Matches 51 - 100 out of 9,921

Document Document Title
WO/2020/202867A1
A high-temperature component according to one embodiment requires cooling performed via a cooling medium, wherein: the high-temperature component comprises a plurality of first cooling passages through which the cooling medium can flow, ...  
WO/2020/201644A2
The present invention relates to the field of aeronautics and more particularly to a high-lift device and an aerodyne comprising such a high-lift device and an aircraft safety device (ASD). The present invention relates to a novel high-l...  
WO/2020/193926A1
The invention relates to a method for removing webs (2) formed on a wall (12) of a central canal (11) of a solid-propellant charge (1), characterized in that the method comprises a step (110) of removing webs (2) by shaving the wall (12)...  
WO/2020/196579A1
A laser ignition device (1) is provided with an excitation light source (2) for generating excitation light, and a pulsed laser oscillator (4) connected to the excitation light source, wherein the pulsed laser oscillator generates a plur...  
WO/2020/193905A1
The invention relates to a counter-rotating turbine (22) of an aircraft turbomachine (10), comprising: - a casing (34) comprising an endoscopy port (40) configured for an endoscopy plug (58) of a non-destructive testing device (60) to pa...  
WO/2020/193925A1
A jet nozzle (100) comprises a combustion chamber (110) which has a downstream end (111) and a divergent nozzle section (120) made of a cone-shaped wall (121) extending between an upstream end (122) and a downstream end. The upstream end...  
WO/2020/193919A1
Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third turbomachine control quantity, each of which can become saturated as a function of the turbomachine operating ...  
WO/2020/195792A1
Provided is a canned motor in which gasification of a liquid being handled, occurring when a rotor is rotating at high speed, is reduced. A canned motor 10 includes: a stator 18 disposed in a stator chamber 26; a rotor 14 disposed in a r...  
WO/2020/188200A2
The invention relates to a nacelle (10A) for an aircraft bypass turbomachine (100), comprising: - an annular envelope (11) extending about a longitudinal axis (104), - a thrust reverser (13) comprising: o an annular movable cowl (14) sit...  
WO/2020/190150A1
Propulsion device in which a main duct (20) which runs over into several branch ducts (7) for flowing media, is enclosed by a housing (5) with at least one inlet opening (4), the branch ducts (7) which are arranged adjoining each other a...  
WO/2020/188177A1
The invention relates to a method for regulating a temperature of the exhaust gases of a turbomachine (1), the method comprising the following steps: - regulating the injection of fuel into a combustion chamber (5) of the turbomachine (1...  
WO/2020/188197A2
The invention relates to an assembly for a turbomachine extending along an axis (X) and comprising: - a ferrule (32) designed to define a fan duct (5) of a gas stream of the turbomachine, - a fan casing (2) radially surrounding the ferru...  
WO/2020/183088A1
This method for monitoring a status of a reducer of a gas turbine comprises the following steps: - obtaining (F10) measurements of parameters realised during an operating phase of the gas turbine, said parameters comprising temperatures ...  
WO/2020/183074A2
The invention relates to a turbine comprising a first rotor (22a) and a second rotor (22b) that can turn in opposite directions and intermesh. The turbine also comprises a ring (66) to which abradable material (68) is fixed, the ring (66...  
WO/2020/183104A1
Aircraft air conditioning system comprising a thermal management system supplied with air, referred to as pressurized air (12), by at least one compressor (14) of the aircraft, and supplied with non-pressurized flow air (206; 208) coming...  
WO/2020/186107A1
A method in a spacecraft for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the th...  
WO/2020/183109A1
The invention relates to a portion of a turbofan (1) extending about a longitudinal axis (A), comprising: - an outer wall (Pe) and an inner wall (Pi), defining a secondary duct portion (Vs), - a cascade of guide vanes (OGV), each guide v...  
WO/2020/181117A1
To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant in...  
WO/2020/176621A1
A linear actuator lock apparatus (500) comprises a housing (410) having an inner surface (502) defining an axial cavity (504) including a first housing portion (506) where the axial cavity has a first lateral size, a second housing porti...  
WO/2020/174162A1
The invention relates to a sandwich panel (10) for an aircraft turbojet nacelle (100), comprising: - a skin, termed outer skin (14, 141), intended to be contact with an air flow, - a skin, termed inner skin (12, 120, 121, 122, 123), oppo...  
WO/2020/169499A1
Disclosed is a stator wheel of a turbomachine intended to be mounted in an aircraft, the turbomachine extending along an axis X, the turbomachine comprising a primary flow path for a first flow of air and a secondary flow path for a seco...  
WO/2020/165527A1
The invention relates to a turbomachine blade (54) comprising a body (60) that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall (66), an upper surface wall (68), a ...  
WO/2020/165532A1
The invention relates to a closing system of a pair of doors (12a, 12b) for a thrust reverser (10) of an aircraft nacelle, the doors being pivotably mounted between a direct-jet position and a reverse-jet position, the closing system com...  
WO/2020/165533A1
A system (30) for controlling a thrust reverser for a nacelle comprising at least one maneuvering actuator (100) arranged to maneuver a door between the direct jet and reversed jet positions, at least one locking means (111) by means of ...  
WO/2020/155460A1
Disclosed are a method for flight on the moon and a flight device using the method. A medium on the surface of the moon and a medium accelerating unit are adopted in the flight method. Under the action of electric power, the medium accel...  
WO/2020/154809A1
A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion ...  
WO/2020/157418A1
The invention relates to an aircraft turbomachine casing (10) having: a substantially cylindrical wall (11) extending along a longitudinal axis, an annular sound insulating shell (12) that is mounted radially inside said wall and is subs...  
WO/2020/152418A1
The invention relates to a noise reducing device (18) for an aircraft turbine engine, said device having a structure in the form of a stack of layers (20, 22, 24), such that a first and a second skin (22, 24) made of composite material f...  
WO/2020/147860A1
A method for forming a nozzle component of an aerospace engine comprises the following steps: step 1, cutting a sheet (1) to obtain a plurality of coaxial truncated hollow cones (3); step 2, performing spinning and straightening on the t...  
WO/2020/148493A1
The invention relates to an aerodynamic arm (100) for an aircraft turbine engine casing, characterised in that it comprises: - a tubular outer shell (110) having a generally elongate shape extending substantially along an axis (A-A), the...  
WO/2020/146928A1
A device for passively reversing a flow of pressurized fluid and capturing the impulse thereof does not comprise movable parts and is disposed as a passive element at the outlet of an external power device that generates reactive thrust,...  
WO/2020/123000A3
Fuel injector system capable of providing fuel into a jet engine operating at hypersonic speeds. The system includes a fuel injection strut (110) extending between opposing walls of an inlet to the engine, and a porous surface extending ...  
WO/2020/143097A1
A system for treating fuel jet plume exhausted from a motor is used to treat fuel jet plume exhausted from a motor. The motor comprises an injector (94) for expansion and acceleration of a fuel gas. The system for treating fuel jet plume...  
WO/2020/112200A3
A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, ...  
WO/2020/142335A1
Technologies for providing noise shielding are described herein. In some examples, noise shields are installed proximate to one or more of the main engines of the aircraft. The noise shields can be extended during terminal operations and...  
WO/2020/136684A1
This patent discloses system for generating additional thrust from the turbine of an exoskeletal turbofan jet engine. System consists of externally located rim driven ducted propeller coupled to the inner rotary drum of the exoskeletal t...  
WO/2020/134005A1
Provided is a throat offset pneumatic vector nozzle having an asymmetric rear body profile, comprising a nozzle body, the rear body profile of the nozzle body being arranged as an asymmetric structure. Under normal circumstances, upper a...  
WO/2020/126848A1
The invention relates in particular to a power plant assembly, comprising - a turbine (TT) for driving at least one rotor shaft (RS); - a combustion chamber (76) for generating drive energy for the turbine (TT); - at least one electric m...  
WO/2020/072111A3
A system and method is disclosed for improving the performance of pulsejet engines and of flight vehicles that incorporate pulsejet engines as a propulsion system. The system and method will decelerate the oncoming airstream to which a U...  
WO/2020/123601A1
A combustion chamber liner comprising a plurality of spiral cooling channels is formed from a material component. A combustion chamber liner body extends from a first end and a second end. The combustion chamber liner body comprises a co...  
WO/2020/120249A1
Power device based on alkali-water reaction, having a reaction chamber (1) to carry out a chemical reaction between water and alkali element, comprising an exhaust nozzle (13) to exhaust the reaction products generated in the reaction ch...  
WO/2020/115382A1
The invention relates to an engine assembly (200) for an aircraft comprising a bypass turbomachine as well as a turbomachine attachment pylon (202) comprising an air-oil exchanger system (30) arranged in an inter-ducts compartment (22) b...  
WO/2020/115403A1
Solid booster (14) for a launcher, the booster being suitable for being separated from the rest of the launcher and comprising a wall (18) defining a combustion chamber (19) comprising an end, termed a front end (19a), and an opposite en...  
WO/2020/115397A1
The device (1) for damping a fluid intended for a reservoir (6) in particular of a spacecraft comprises a framework (3) provided with at least one ring (8) and with a plurality of rods (7), each of said rods (7) being fastened by a first...  
WO/2020/115424A1
The invention particularly relates to a thrust reverser (1) comprising a fixed (2) and mobile (3) structure defining an air stream, a flap (4) comprising a single wall (40) perforated on the surface thereof, and comprising a structure (4...  
WO/2020/055220A9
A self-propelled vehicle which can be configured in the form of an aircraft and comprises a central system of compartments, working members, and a drive comprising the following components: a source of energy, a transmission mechanism, c...  
WO/2020/109705A1
The invention concerns a turbofan engine comprising an exhaust casing (21) traversed by a primary flow (FP) and surrounded by a secondary flow (FS) and an outlet cone (23) carried by this exhaust casing (21), the exhaust casing and the o...  
WO/2020/111622A1
The present invention relates to a hybrid rocket engine using an electric motor-driven oxidizer pump, wherein an overheated electric motor and battery are cooled by a low temperature oxidizer, and pressure generated from the vaporization...  
WO/2020/107844A1
An infrared enhancer with controllable radiation power, relating to the field of unmanned aircraft, and capable of solving the problem of the difficulty of controlling the radiation power of infrared enhancers. The infrared enhancer comp...  
WO/2020/112200A2
A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, ...  

Matches 51 - 100 out of 9,921