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WO/2021/126186A1 |
A system for attaching an aft portion of an aircraft engine to an aircraft structure includes a base mount, a linkage arm that is arranged between opposing inner surfaces of the base mount and moveably attached to the base mount at least...
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WO/2021/120093A1 |
A firefighting system of a turbine engine (7). The firefighting system comprises a firefighting material storage unit (1), a control unit (3), a control box (4), a pipeline unit (5), and a firefighting monitoring unit (6). The firefighti...
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WO/2021/121976A1 |
The invention relates to a gas turbine engine (1) of an aircraft, comprising an inner engine region (27) and an outer engine region (28), which delimit a flow cross-section (2) and are operatively interconnected by means of braces (22, 2...
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WO/2021/116600A1 |
Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first t...
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WO/2021/116621A1 |
The present invention relates to an aero-propulsion system (1) comprising: - a drive shaft (10), - a low-pressure compressor (4), - a fan shaft (13) driving a fan (2), - a reduction mechanism (12) coupling the drive shaft (10) and the fa...
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WO/2021/116591A1 |
The invention relates to a heat exchanger (16) between a fluid and an air flow (FS), comprising a heat exchange wall (17) separating the fluid and the air flow (FS), the heat exchange wall (17) having a heat exchange surface (18) which e...
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WO/2021/116556A1 |
Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bear...
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WO/2021/116570A1 |
Disclosed is a hydraulic equipment plate (40) for an aeronautical turbomachine comprising channels for fluids to flow into and out of each of the pieces of hydraulic equipment (44, 46, 48, 50, 52), further comprising a part supporting a ...
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WO/2021/116620A1 |
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) comprising two reduction stages (27, 32) and including: - a sun gear (33), ...
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WO/2021/116592A1 |
The invention relates to an assembly for a turbomachine through which an air flow flows, comprising a stator (6) having guide vanes (7) that extend radially relative to a longitudinal axis (AX), at least one inter-vane platform (19) that...
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WO/2021/116578A1 |
Turbomachine (10) with a counter-rotating turbine for an aircraft, the turbomachine comprising a counter-rotating turbine (22) and a mechanical reduction gear (42) with an epicyclic, planetary-type gear train which comprises a planet car...
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WO/2021/115996A1 |
Auxiliary power unit, in particular for an aircraft, comprising a gas generator (12) and an electric generator (20) comprising an input shaft (20a) connected to an output shaft (14a) of the gas generator (12). The auxiliary power unit co...
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WO/2021/116557A1 |
Aircraft turbine engine (10), comprising: - at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V), - an annular exhaust casing (28) supporting at least one bear...
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WO/2021/116622A1 |
The present invention relates to an aeronautical propulsion system (1) comprising: - a reduction mechanism (12) coupling a drive shaft (10) and a fan shaft (13) and comprising two reduction stages (27, 32) comprising: a sun gear (33), a ...
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WO/2021/113429A1 |
A fuel nozzle metering valve that includes a spool having an inlet port and an outlet flow port, and a retainer assembled to one end of the spool. A valve liner houses a portion of the spool. The spool is configured to move back and fort...
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WO/2021/113459A1 |
A computer-implemented method for multi-mode operation of a combustion system (100) and a combustion system (100) are provided. The method includes initializing combustion of a fuel/oxidizer mixture (132), determining whether conditions ...
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WO/2021/113465A1 |
A rotating detonation combustion (RDC) system (100) is provided. The RDC includes a first outer wall (118) and a second outer wall (119) each extended around a centerline axis (117), and a detonation chamber (122) formed radially inward ...
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WO/2021/108001A1 |
An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity ...
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WO/2021/105022A1 |
An air inlet into a nacelle of an aircraft turbojet engine comprises a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall (21) and an outer ...
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WO/2021/105595A1 |
The invention relates to a resonating patch (20) for acoustic treatment, comprising a resonant plate (21), a transducer (22) and an electrical circuit (23) electrically connected to the transducer (22), the resonant plate (21) comprising...
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WO/2021/103935A1 |
Provided is a fuel gas inlet adjusting system for a gas turbine with co-combustion gas injection and heat value adjustment functions, the system comprising a natural gas injection pipeline (1), a main synthetic gas main pipeline (2) and ...
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WO/2021/099482A1 |
The present invention relates to a front centre body (FCB) structure for a geared turbofan engine. The FCB comprises a plurality of vanes extending across the inlet duct to the low pressure compressor and integrates a heat exchanging arr...
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WO/2021/101957A1 |
A rotating machine assembly includes a rotating machine that has a cover that defines an outer surface of the rotating machine and a stator disposed within the cover. The stator is stationary with respect to the cover. The rotating machi...
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WO/2021/099752A1 |
The document relates to a device for supplying fuel to a combustion chamber of a gas generator, comprising: - a wheel (14) for injecting fuel into the combustion chamber (18), - a fuel supply rail (20) comprising an internal fuel circuit...
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WO/2021/096366A1 |
A gas turbine engine comprises at least a power output turbine unit (POT) (300) which is rotatably arranged inside an outer housing unit (200), and a compressor-turbine unit (CTU) (400) which is rotatably arranged inside the POT (300), a...
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WO/2021/094677A1 |
Disclosed is an impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, the impeller (230) being intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reduc...
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WO/2021/093806A1 |
An intelligent self-checking gas turbine based on variable fuzzy membership degree, comprising a gas unit. The gas unit comprises a housing (1) and a gas pipeline (2) fixedly mounted at one end of the housing (1) and communicated with th...
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WO/2021/090807A1 |
A combustor structure (1) of an embodiment is arranged so as to pass through a casing of a supercritical CO2 gas turbine, which uses super critical CO2 in a working fluid, from a direction perpendicular to the axial direction of a turbin...
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WO/2021/089933A1 |
The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts an...
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WO/2021/086715A1 |
Method and system for transitioning from a first liquid fuel supplied to a combustor of a gas turbine system to a second liquid fuel supplied to the combustor utilizing a fuel pump configured to supply both fuels from the fuel pump durin...
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WO/2021/084206A1 |
The present invention relates to an acoustic attenuation panel (1) comprising: - a cellular structure (10) comprising a plurality of acoustic cells (100) separated from one another by peripheral partitions (102), - a perforated acoustic ...
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WO/2021/084389A1 |
A gas turbine engine is provided with a split recuperator system which includes at least two heat exchangers connected by one or more ducts through which a high density fluid transfers thermal energy. The specific heat capacity and visco...
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WO/2021/083237A1 |
A mixed heating system for a syngas fuel of an IGCC power station gas turbine and a method, the system comprising: a syngas pipe (1), a water vapor main pipe (2), a first water vapor secondary pipe (3), a second water vapor secondary pip...
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WO/2021/079048A1 |
A turbomachine comprises a rotary body comprising a drive shaft delivering mechanical power. The turbomachine comprises an electromagnetic pump (100) mechanically decoupled from the drive shaft. The electromagnetic pump comprises at leas...
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WO/2021/079657A1 |
Provided is a liquid fuel injector that can improve ignitability under operating conditions where the air flow rate is low and combustion stability under a wide range of operating conditions.　The liquid fuel injector comprises: a cylin...
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WO/2021/079890A1 |
This gas turbine engine comprises a main flow channel that guides compressed air extracted from a compressor to a bearing, and an oil supply device that includes an oil tank in which oil is stored and that supplies the oil to the main fl...
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WO/2021/079891A1 |
This gas turbine engine is provided with: a main flow path for guiding compressed air bled from a compressor to a bearing; and an oil supply apparatus for supplying oil to the main flow path, wherein the oil supply apparatus has a pressu...
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WO/2021/073984A1 |
The invention relates to a planetary gearbox (30) in a gas turbine engine (10), wherein a plurality of planetary gears (32) are each mounted on a planetary gear bearing journal (51) by a slide bearing (50), characterized in that a bushin...
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WO/2021/074531A1 |
Disclosed is a method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request (100) by a pilot of the helicopter to quickly stop the engine, the following steps managed by the control unit...
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WO/2021/074521A1 |
The invention relates to a propulsion unit (1) comprising: a gas generator (100) comprising: *a compressor (110), *a combustion chamber (120), *a turbine (130), at least two compressed-air propulsion modules (200), each propulsion module...
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WO/2021/074609A1 |
An air inlet for an aircraft nacelle comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface ...
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WO/2021/074535A1 |
The invention relates to an assembly for a turbomachine, comprising: - a nacelle comprising an inlet lip which defines an air inlet, and - a device for modifying the geometry of the air inlet, comprising: - a first spout, and - a second ...
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WO/2021/073956A1 |
The invention relates to a vehicle (1) comprising: - a fairing (2); - at least one propeller, characterized in that the fairing (2) defines a fluid chamber having a main opening that opens onto a lower face (22) of the fairing (2) so as ...
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WO/2021/074536A1 |
The invention relates to a method for repairing a turbomachine air intake lip comprising a damaged region of which the shape differs from the initial shape of the lip, characterized in that it comprises: - a step (41) of identifying the ...
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WO/2021/069838A1 |
The present invention relates to a turbine injector (1) comprising an annular ring (10) extending around a longitudinal axis (A) and having a radially outer edge (12) and a radially inner edge (14). The crown (10) has a plurality of chan...
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WO/2021/071850A1 |
A mobile source of electricity is converted from a transportation mode to an operational mode. A turbine disposed on the mobile source of electricity is operated to generate electricity in the operational mode. A first control valve is o...
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WO/2021/067365A1 |
Heat exchangers, heat exchanger systems, and hypersonic vehicles are provided. For example, a heat exchanger is provided that comprises a first chamber for receipt of a flow of cool fluid and a second chamber for receipt of a flow of hot...
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WO/2021/065100A1 |
This electricity generator is provided with a rotor (31) which is attached to a rear end portion (17a) of a low-pressure shaft (17) that is rotatably supported by a bearing (29) in a multi-shaft gas turbine engine (10), and that links a ...
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WO/2021/064396A1 |
A thermal management system is provided for managing the temperature of one or more components in an aircraft nacelle. The thermal management system comprises an inlet opening into the nacelle, an outlet opening out of the nacelle, a gas...
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WO/2021/066121A1 |
A combustor for gas turbine according to at least one embodiment of the present disclosure comprises a first burner in which a plurality of first nozzles are provided along the inner periphery of a cylindrical combustion cylinder; and a ...
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