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WO/2024/009024A1 |
The invention relates to a propulsion unit comprising: an electric motor (10), which includes an annular stator (11) about a longitudinal axis (X) and a rotor arranged radially inside the stator (11), so as to be rotated about the longit...
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WO/2024/009021A1 |
The invention relates to a method for controlling a hybrid turbine engine (11) for an aircraft, the turbine engine (11) comprising a low-pressure shaft (10), a high-pressure shaft (9), at least one power conversion device (13) mounted on...
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WO/2024/009020A1 |
Disclosed is a twin-spool turbomachine comprising a low-pressure turbine (5) connected to a low-pressure compressor (1) by a low-pressure rotation shaft (10) and a high-pressure turbine (4) connected to a high-pressure compressor (2) by ...
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WO/2024/008781A1 |
The invention relates to an injector for a rocket engine, comprising a main part (10, 12) in which a fuel feed and an oxidator feed are provided and comprising an adjusting element (20) which, in cooperation with the main part (10, 12), ...
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WO/2024/006185A1 |
A redundant fuel metering system and method for a multi-stage combustor that utilizes a fuel metering valve EHSV from a less critical combustor stage fuel metering system as a redundant backup to the main metering valve EHSV. In the even...
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WO/2024/003083A1 |
The invention concerns an aircraft fuel heating arrangement comprising an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more cond...
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WO/2024/003756A1 |
For example, a controller of an Active Acoustic Control (AAC) system may be configured to process input information including AAC configuration information, and a plurality of noise inputs representing acoustic noise at a plurality of no...
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WO/2024/002034A1 |
A fixing device for temperature sensors in a combustion chamber of a solid rocket engine, comprising anti-static materials (1) and an elastic supporting part. The two anti-static materials (1) are fixedly installed at two ends of the ela...
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WO/2024/006730A1 |
Dynamic ram accelerator operation permits operation with lower acceleration, permitting launch of acceleration sensitive payloads such as crewed vehicles. Operational cost is reduced, and reliability improved, by reducing or eliminating ...
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WO/2023/247893A1 |
The invention relates to a blocker door for a thrust reverser, preferably having screens and a sliding cover, the blocker door comprising: a structural frame (14) which is configured to ensure the mechanical strength of the blocker door;...
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WO/2023/249660A1 |
An integrated hydrogen-electric engine includes, an air compressor system; a hydrogen fuel source; a fuel cell; an elongated shaft connected to the air compressor system or a propulsor; and a motor assembly disposed in electrical communi...
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WO/2022/173709A9 |
An expendable launch vehicle is provided using pressure-fed liquid propellant fixed steering ablatively-cooled rocket engines. The vehicle is manufactured minimizing toxic or exotic metals and maximizing the use of conventional, inexpens...
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WO/2023/246980A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine ...
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WO/2023/245874A1 |
A solid propellant pressure-coupled response function measurement method, a mold for processing an end combustion surface charge and a mold for processing a cup-like charge. Two charges having different sizes of combustion surfaces are d...
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WO/2023/247883A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion unit, the reverser comprising a stationary structure (31) and a movable structure (29) comprising at least one movable reverser cover (33) delimiting the secondar...
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WO/2023/249659A1 |
An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell, a heat exchanger, an elongated shaft, a motor assembly and a combustion chamber including a turbine downstream of the fuel ce...
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WO/2023/242496A1 |
The invention relates to an assembly for a turbine engine of longitudinal axis (X), comprising: an exhaust cone (40) having an annular wall (44); an exhaust casing arranged upstream of the exhaust cone (40); a connection flange (46) disp...
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WO/2023/241021A1 |
A gas jet split stream-type rotor supercharged gas turbine, which comprises a gas compressor (21) and a turbine (23) connected by means of a mechanical shaft; a rotor (25) having multiple rows of combustion chambers (26) is arranged betw...
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WO/2023/237152A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) with a main flow channel (10) and a bypass flow channel (20), a water system (30) and a steam system (40), wherein the water system (30) compr...
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WO/2023/237151A1 |
A propulsion system (1) for an aircraft, comprising a gas turbine (2), with a main flow duct (10) and a bypass flow duct (20), wherein the gas turbine (2) has an outer housing (5) which surrounds the bypass flow duct (20) on the outside....
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WO/2023/221250A1 |
A coaxial liquid-propellant rocket engine using a full-flow staged-combustion cycle, comprising a turbopump system (10), a propellant injection system (20), and a thrust chamber (30) which are correspondingly arranged. The turbopump syst...
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WO/2023/222972A1 |
The invention relates to a thrust reverser (30) for an aircraft propulsion unit, comprising a fixed structure (31) equipped with a wall (18) for radially internally delimiting a secondary flow duct (21B), and a mobile structure (29) comp...
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WO/2023/220311A1 |
An ejector system is constructed of a soft yet strong material such as silicone-based material which can be pressed to conform within a small space and stowed when inactive and can be expanded or stretched by mechanical, pneumatic or hyd...
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WO/2023/216762A1 |
A deflagration engine having an air intake end not in communication with a fixed combustion chamber, the deflagration engine comprising an air intake duct, a bearing, a shaft, and an aircraft. The deflagration engine further comprises a ...
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WO/2023/213420A1 |
The invention relates to a, preferably pumpless, pressure fed propulsion system for a spacecraft, preferably a satellite or microsatellite, the system comprising: - a propellant tank (101) for storing a propellant; - a first heat exchang...
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WO/2023/209707A1 |
A system for generating hot, high-pressure exhaust gas for thrust includes an energetic powder monopropellant, wherein each particle of powder is comprised of a combination of oxidizer and fuel in a ratio suitable for combustion; and a r...
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WO/2023/209337A1 |
There is provided an acoustic black hole comprising: in a first axis, along a line, a variation from a first characteristic to a second characteristic to a third characteristic, wherein the acoustic black hole comprises a taper from the ...
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WO/2023/209339A1 |
There is provided an acoustic black hole comprising: in a first axis, a variation from a first characteristic to a second characteristic, along a line; in a second axis different to the first axis, a variation from a first characteristic...
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WO/2023/209338A1 |
There is provided an acoustic black hole comprising: in a first axis, a taper from a first thickness to a second thickness, along a line; in a second axis perpendicular to the first axis, and away from the line, one or more regions of di...
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WO/2023/209290A1 |
The invention relates to an assembly for a turbine engine having a longitudinal axis (X), the assembly comprising a first structural element (51) and a nut device (60), the first structural element (51) comprising a first hole (54) and a...
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WO/2023/203122A1 |
An air/oil heat exchanger (40) is provided in a vein (16). The exchanger (40) comprises parietal channels (60, 62) and central channels (64), the radial height (H60, H62) of the parietal channels increasing from the inlet (40.1) of the e...
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WO/2023/203118A1 |
An air/oil heat exchanger (40) is provided in a vein (16). The exchanger (40) comprises inner parietal channels (60) and/or outer parietal channels (62) and central channels (64), the radial height (H60, H62) of the inner and/or outer pa...
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WO/2023/203121A1 |
An air/oil heat exchanger (40) is provided in a vein (16). The exchanger (40) comprises parietal channels (60, 62) and central channels (64), the radial height (H60, H62) of the parietal channels being less than the radial height (H64) o...
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WO/2023/198962A1 |
The invention relates to a triple-flow turbine engine (10) for an aircraft, this turbine engine having a longitudinal axis (X) and comprising: - upstream suspension elements (48) which are located in a first plane (P1) perpendicular to t...
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WO/2023/198963A1 |
The invention relates to a multiple-flow turbine engine (10) for an aircraft, said turbine engine comprising a gas generator (12) having geometric characteristics allowing it to have, on the periphery thereof, a cold compartment (C2) tha...
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WO/2023/198999A1 |
The invention relates to a sound absorber (100) extending between two opposite surfaces (100a), (100b) and combining one or more quarter-wave acoustic resonators (102), (102') with a microporous element (101). Each acoustic resonator (10...
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WO/2023/196553A1 |
Aircraft engines and methods of operation include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the bu...
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WO/2023/193558A1 |
Disclosed in the present application are a flow guide structure and device for measuring the uniformity of a cooling path jet, which structure and device relate to the technical field of liquid rocket engines, and solve the problem of it...
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WO/2023/194665A1 |
The invention relates to a gas turbine (110) comprising - two unducted propellers; - a main duct (171); - at least one compression stage (145) located in the main duct (171); - a cooling duct (173) extending from a cooling inlet and open...
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WO/2023/192059A1 |
A rocket motor (18) has an energetic material (22) between solid fuel (propellent, 28) and a casing (24) that surrounds the solid fuel. The energetic material is configured to be burned along with the solid fuel during normal operation o...
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WO/2023/192061A1 |
A rocket motor includes at least one inert rod. The inert rod has a groove that extends along the length of the inert rod. The groove may be machined by a lathe, die, and/or CNC machine, such that the groove is configured helically aroun...
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WO/2023/191363A1 |
The present invention relates to: a roll control thruster for using a portion of oxidant, discharged from an electric motor pump after cooling, as a propellant for the roll control thruster; and a hybrid rocket provided with same. To thi...
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WO/2023/180381A1 |
The present invention relates to an electrically driven ducted fan engine (10), comprising a housing (12) with an inner housing wall (12a), defining a substantially cylindrical inner space (14) and a longitudinal axis (L), an inlet openi...
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WO/2023/183167A1 |
A method for managing propellant in a spacecraft is disclosed. The method includes storing liquid propellant in a tank under an operating pressure controlled using a product of chemical decomposition of the propellant. The method may inc...
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WO/2023/179343A1 |
A pintle injector, comprising a housing, a central cylinder, a central rod, and a pintle. The central cylinder is located in the housing and is fixedly connected to the housing. The pintle is located between the housing and the central c...
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WO/2023/175257A1 |
The present invention relates to an assembly for a turbomachine having a longitudinal axis (X), comprising: - an exhaust cone comprising an outer annular wall (102) for the flow of a primary air flow made of a ceramic matrix composite ma...
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WO/2023/175260A1 |
Dismountable aeronautical pod device 30 with cryogenic storage capacity, for external transportation by an aircraft, comprising a front cryogenic tank 36, a rear cryogenic tank 37, and at least one central temporary storage tank for the ...
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WO/2023/177942A1 |
A monopropellant rocket thruster includes a thruster, a pump, a decomposition catalyst, and an igniter. The thruster housing includes a reaction chamber and a divergent nozzle. The pump, coupled to the thruster housing, is operable to pu...
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WO/2023/175271A1 |
The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises at least a first electric machine (300) and a gas turbine engine (200). The gas turbine engine (200) comprises a low-pre...
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WO/2023/175625A1 |
The present invention relates to a low density peroxide cured EPDM rubber based insulation suitable for use in large composite rocket motor casing (CRMC), which uses only conventional filler. The said insulation can be used in large CRMC...
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