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WO/2022/118208A1 |
A spacecraft is equipped with a low and high thrust space propulsion system including at least one water reservoir (1) containing liquid water, a high thrust propulsion part and a low thrust propulsion part. The high thrust propulsion pa...
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WO/2022/117934A1 |
The invention relates to a scoop (30) for an aircraft turbine engine (10), this scoop comprising a body (40) which is movable between at least two positions, including a first position in which it is configured to capture part of a first...
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WO/2022/114755A1 |
An electric motor-integrated rocket engine pump is provided. The electric motor-integrated rocket engine pump may comprise: a housing; a rotating body provided in one direction inside the housing; an electric motor provided inside the ho...
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WO/2022/115124A1 |
A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated pro...
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WO/2022/111968A2 |
An electric heating system for heating a fluid flow, the system comprising: a housing having an inlet for a fluid flow to be heated by the electric heating system and an outlet for the fluid flow which has been heated by the electric hea...
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WO/2022/108197A1 |
The present invention relates to a combustor including a heat exchange structure and a rocket comprising same. The combustor according to an embodiment of the present invention comprises: an inner wall; an outer jacket arranged to cover ...
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WO/2022/105212A1 |
A gas-blown miniature gas turbine, comprises a gas compressor (1), a turbine (2), a rotating shaft (3), a gas inlet channel (4), and a combustion chamber (5). The gas compressor (1) and the turbine (2) are sleeved on the front end and ta...
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WO/2022/107172A1 |
Disclosed is a multi-contour duct (100) including a front part (102) configured to entrain ambient air, an intermediate part (104) configured to convert the pressure head into the velocity head for the entrained air and a rear part (106)...
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WO/2022/103511A1 |
An air-breathing rocket engine in certain embodiments comprises an outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake and an annular primary...
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WO/2022/103585A1 |
A compact heat exchanger (170) is disclosed for re-circulating bleed air from a combustor into an inlet (110) and/or exhaust (150) of a gas turbine engine (100). In an embodiment, the heat exchanger (170) may comprise a plurality of airf...
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WO/2022/100531A1 |
An auxiliary propulsion device for an aerospace liquid propeller comprising a main propulsion device, a left auxiliary device (3), and a right auxiliary device (10). The main propulsion device comprises a housing (1). A thermal insulatio...
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WO/2022/096821A1 |
The present disclosure relates to an assembly for a turbomachine nozzle having a longitudinal axis (X), comprising: an exhaust cone (100) comprising an annular outer wall (102) for guiding a primary air flow and an annular chamber (106) ...
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WO/2022/096822A1 |
The invention relates to an assembly for a turbomachine, comprising an exhaust cone (18) and an exhaust case having an annular inner shell, the exhaust cone (18) and the exhaust case extending about an axis (X), the exhaust cone (18) hav...
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WO/2022/096823A1 |
The invention relates to an assembly for a turbomachine (1) comprising an exhaust cone (18) and an exhaust casing (17) comprising an annular inner shell (19), the exhaust cone (18) and the exhaust casing (17) extending about an axis (X),...
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WO/2022/096820A1 |
The invention relates to an assembly for a turbine of a turbomachine having a longitudinal axis (X), comprising: - an exhaust cone (100) comprising an annular outer wall (102) for a stream of a primary airflow and an annular chamber plac...
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WO/2022/096837A1 |
A rear part for a turbojet engine comprises a variable-geometry nozzle in which a convergent flap is provided with a lever (80) supporting a bearing roller (96) arranged axially between an upstream bearing wall (90) and a downstream bear...
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WO/2022/096815A1 |
Disclosed is an aircraft dual-flow turbine engine assembly (32) comprising: • - an internal shroud (42) for externally delimiting a primary flow path (16) of the turbine engine gases; • - an external shroud (40) for internally delimi...
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WO/2022/096838A1 |
A turbine engine rear part comprises a variable-geometry nozzle comprising a synchronizing ring (82), drive means for effecting longitudinal translation of the synchronizing ring relative to an upstream stator structure (38), and connect...
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WO/2022/096832A1 |
The present disclosure relates to an assembly for a turbine of a turbomachine having a longitudinal axis, the assembly comprising: an exhaust cone (102) comprising an annular outer wall (104) for a stream of a primary airflow and an annu...
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WO/2022/096825A1 |
The present disclosure relates to an assembly for a turbine of a turbomachine having a longitudinal axis, comprising: - an exhaust cone comprising an annular outer wall for a stream of a primary airflow and an annular chamber, an exhaust...
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WO/2022/090643A1 |
A fairing element (33) is intended to be placed in a fluid flow passage (F), to surround an obstacle (31) which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairi...
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WO/2022/093301A1 |
An integrated propulsion and warhead system (22) for an artillery round (10) includes a propulsion system (24), such as a solid rocket motor (32) and/or an air-breathing jet engine (34), and an annular explosive (26) concentrically arran...
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WO/2022/090914A1 |
The present disclosure provides a device for propulsion in a vehicle. The device comprises an inlet for allowing a fluid, a power module provided for accelerating the fluid, a vector thrust mechanism fluidly connected to the power module...
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WO/2022/090674A1 |
Disclosed is a turbomachine turbine assembly (48) having a longitudinal axis and comprising: - an exhaust casing (30), - an ejection cone (40) arranged downstream of the exhaust casing (30), the ejection cone (40) comprising an outer ann...
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WO/2022/090660A1 |
The invention relates to a method for repairing a part (1) for an aircraft turbine engine, the part (1) comprising a lower panel (3), an upper panel (2) and a core (4) having a honeycomb structure arranged between the lower panel (3) and...
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WO/2022/084615A1 |
The present invention relates to a blade (3) of a fan (1), made of composite material, of a turbomachine. On a portion (15) of the blade (7) which extends from a lower limit (16) located at a predetermined distance (d) from the shank (6)...
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WO/2022/086587A1 |
A multi-pulse propulsion system (10) includes at least one pulse chamber (20) containing at least one propellant (22) for igniting during at least one pulse of the multi-pulse propulsion system, at least one additional pulse chamber (24)...
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WO/2022/085033A1 |
Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to...
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WO/2022/079378A1 |
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13), and an inlet channel (3) comprising an inner shroud (16) having a predeter...
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WO/2022/079386A1 |
This system (101) includes: - a thrust-reversal cowling (112) designed to be selectively moved between a retracted position for leaving unchanged the thrust of a turbine engine (102) of the aircraft (100), and a deployed position for rev...
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WO/2022/081455A1 |
The subject matter of this specification can be embodied in, among other things, an actuator apparatus includes an output member configured to actuate between a first positional configuration and a second positional configuration, a sour...
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WO/2022/081759A1 |
Various embodiments of a vortex thruster system is described herein that are configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system includes a catalyst bed configured to decompose a mo...
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WO/2022/079368A1 |
An injector for simultaneously injecting at least two fluids into a chamber comprises at least one injection element (10) which is capable of receiving the fluids separately via an axial conduit (1) and via at least one lateral channel (...
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WO/2022/081569A1 |
An electrically decoupled jet engine. The electrically decoupled jet engine includes a combustion chamber which creates a toroidal flow of air and a rotational electric motor which drives a fuel supply into the combustion chamber. The to...
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WO/2022/077079A1 |
The present invention patent application relates to a method using real pressure, temperature and mass data obtained from real telemetry to control the mixing ratio by altering the temperature set in its tanks, wherein, for the purposes ...
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WO/2022/076736A1 |
The present invention comprises a novel autorotation safety device consisting of at least one compressed air tank that is configured to release high velocity air, either autonomously or through the actions of a pilot, into a thrust produ...
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WO/2022/074405A1 |
A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.
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WO/2022/073889A1 |
A supersonic air intake (5) of an aircraft propulsion assembly (8) comprises: • · a pipe (4) with a longitudinal axis (X) configured to guide the flow of air (F) into the turbine engine (7), • · a speed reducer (3) fixedly mounted ...
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WO/2022/074323A1 |
The present invention relatejavascript: document.forms[0].task.value='8515023'; doSubmit('gototask_8515023')s to an assembly for a turbomachine turbine extending along an axis (X), comprising: - an ejection cone (100) comprising a radial...
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WO/2022/069496A1 |
A shell (10) having a body (100) made of a first material, the body (100) comprising an internal wall (11), which is oriented towards the inside of the shell (10) and delimits, at least partially, an internal space (12), the internal wal...
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WO/2022/069835A1 |
The invention relates to a turbomachine module having a longitudinal axis X, comprising a shroudless propeller (2) which is rotated about the longitudinal axis X by a drive shaft (9, 10), which is connected at least to a compressor rotor...
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WO/2022/068703A1 |
A thrust transfer apparatus for an ignition test of a solid rocket engine in a form of rear skirt connection, comprising a front end connecting plate (16), a base (20), a rear skirt connecting plate (14, 17), an arc-shaped seat (12), a c...
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WO/2022/064136A1 |
The invention relates to a heat exchanger (21) comprising a support wall (22) and a first plurality of fins (23) that each stand proud from an outer surface (24) of the support wall (22) and are designed to have a first air flow pass ove...
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WO/2022/057752A1 |
A cryogenic engine suitable for a space apparatus, the engine comprising an injector body (1), a thrust chamber (2), and a spark plug (3). An accommodating space is provided in the injector body (1). The spark plug (3) is mounted on one ...
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WO/2022/058419A1 |
The present invention relates to a solid-body structure such as an engine cowling, a component of a weapon, in particular a barrel or muffler, or any other acoustically effective structure, wherein the solid-body structure is coupled to ...
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WO/2022/058673A1 |
The invention relates to a method for manufacturing a composite material part comprising a cellular structure which comprises at least one cell (21) delimited by walls, the method comprising: supplying at least a first core (40, 40a, 40b...
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WO/2022/058369A1 |
The invention relates to a combustion chamber arrangement (10) with a combustion chamber (20) which is oriented along a longitudinal axis (L), and with an injector arrangement (18) which is arranged on the end side of the combustion cham...
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WO/2022/053759A1 |
The invention relates to a method for manufacturing a part made of composite material comprising a reinforcement area, by thermocompression of a first and a second material, the method comprising the following steps: - depositing the fir...
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WO/2022/055478A1 |
Airframe integrated scramjet engines are disclosed. Scramjet engines within the scope of this disclosure may be configured to integrate smoothly with an airframe of a hypersonic flight aircraft or vehicle. The scramjet engine may include...
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WO/2022/053753A1 |
The present invention relates to a fan blade (1) of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement (4) obtained by three-dimensional weaving of strands (12, 14) and a matrix in which t...
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