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WO/2023/014635A1 |
The present teachings generally include improvements to gas turbines for increasing performance and/or efficiency thereof. In an aspect, a gas turbine system featuring a free turbine includes an injector structurally configured to supply...
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WO/2023/007076A1 |
The invention relates to a device (136) for controlling a power-transfer system (124) for the transfer of power between a high-pressure shaft (108) and a low-pressure shaft (116) of a turbomachine (104) of an aircraft (102), comprising: ...
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WO/2023/007396A1 |
Turbomachine (10) comprising: • - a turbine (2) provided with an turbine wheel • - sealing means (7), designed to prevent lubrication oil from escaping towards the turbine wheel, • - a cooling system (11) exclusively based on heat ...
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WO/2023/001907A1 |
The invention relates to a turbine engine comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downst...
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WO/2023/003490A1 |
The invention relates to the field of aviation, and more particularly to tactical light aircraft having low radar detectability. The technical result consists in increasing the stability and handling properties of an aircraft without neg...
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WO/2023/001379A1 |
The present invention relates to a system (1) for cooling oil in an aircraft turbine engine (100), said system comprising an intermediate support casing (2) intended to be located between a low-pressure compressor (120) and a high-pressu...
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WO/2023/003491A1 |
The invention relates to aviation. A multi-functional supersonic single-engine aircraft comprises a fuselage, a trapezoidal wing, a V-shaped all-moving tail assembly, developed lateral booms, an inferior lateral engine air inlet, dispose...
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WO/2023/001538A1 |
The present invention relates to a system (1) for cooling oil in an aircraft turbine engine (100), said system comprising an intermediate support casing (2) intended to be located between a low-pressure compressor (120) and a high-pressu...
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WO/2023/002121A1 |
The present invention relates to a rotating assembly (10) of a turbomachine (1), comprising: - a shaft (8) configured to drive a propeller (2) of the turbomachine (1) around an axis (X) and comprising a first flange (18) radially extendi...
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WO/2023/286516A1 |
A gas turbine facility comprising: a gas turbine; an ammonia supply device for supplying ammonia to a combustor of the gas turbine; a flow passage forming frame forming an exhaust gas flow passage through which exhaust gas from the gas t...
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WO/2023/286381A1 |
A gas turbine system 1 is provided with: a combustor 13; a suction flow path 101 connected to the combustor 13; an exhaust flow path 102 connected to the combustor 13; a compressor 11a provided in the suction flow path 101; a turbine 11b...
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WO/2023/284146A1 |
An air supply device (100), and a gas turbine system and a method for using same. The air supply device (100) comprises an air intake cabin (110), a combustion air intake filter (121), a combustion air intake silencer (122), a combustion...
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WO/2023/284354A1 |
A ventilation structure of a core chamber of a turbofan engine having a large bypass ratio, said structure comprising: an outer bypass wall surface (1), a core chamber wall surface (4) and a core casing (7). An outer bypass flow channel ...
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WO/2023/285902A1 |
A jet exhaust capturing and containing apparatus for collecting ultrafine particles (UFPs) and gaseous exhaust exiting a jet engine or APU nozzle while in operation near an airport facility where an aircraft is in motion, or at stop, aro...
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WO/2023/281221A1 |
The invention relates to a fire safety system (30) for a turbomachine (1), such as an aeroplane turbofan or a turboprop engine, the turbomachine comprising at least one turbine (3) having a turbine disc (5) and an annular cavity (16) whi...
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WO/2023/283399A1 |
A turbine engine system includes an aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply l...
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WO/2023/281265A1 |
A propulsion system comprising, an ammonia cracking module and an engine module, wherein ammonia is supplied to the ammonia cracking module to produce a fuel blend of hydrogen, nitrogen and ammonia, said fuel blend subsequently being fed...
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WO/2023/276370A1 |
A silencing device according to the present invention includes: a first waveform acquisition unit that, on the basis of a reference signal that detects vibrations at a first position on an exhaust duct of a gas turbine, acquires a first ...
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WO/2023/275836A1 |
Method for manufacturing a core (10) for an aircraft panel (100) with the steps of: arranging first sheet-shaped partitioning elements (12), each with vertical slits (16), extending transversely from a first edge (12a), and transverse sl...
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WO/2023/275839A1 |
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging first sheet-shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first ...
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WO/2023/275454A1 |
The invention relates to a method (200) for controlling a system for generating and controlling power in an aircraft comprising: - a hybrid propulsion system comprising an electrical network and a propulsion-energy source; - at least one...
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WO/2023/275838A1 |
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging a plurality of first sheet- shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transverse...
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WO/2023/275487A1 |
The present invention relates to an assembly for a gas turbine comprising a hollow central shaft (100) which is rotatably guided by at least one bearing (102), the assembly further comprising a device (110) for lubricating said at least ...
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WO/2023/275499A1 |
The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connect...
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WO/2022/270187A1 |
A gas turbine system 100 comprises: an ammonia tank 140 for storing liquid ammonia; an ammonia flow passage 30 which is connected to the ammonia tank 140 to allow the liquid ammonia to flow; a fuel injection nozzle 134 connected to the a...
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WO/2022/270232A1 |
The present invention comprises: a mixing duct (10) equipped with an inlet (10a) through which combustion gas flows in and an outlet (10b) through which the combustion gas flowing in from the inlet (10a) flows out; a cooling duct (40) th...
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WO/2022/264865A1 |
This turbine assembly comprises: a first main body provided with a first protrusion constituting a part of an annular body formed annularly around an axis and protruding radially outward and horizontally from the annular body, and a seco...
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WO/2022/263751A1 |
The invention relates to an acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit (1) in contact with a fluidic flow, the panel (10) comprising a first, acoustically reflective skin (14), a ...
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WO/2022/262998A1 |
The invention relates to a turbomachine (2) of the type having an unducted fan (4), comprising: a splitter (10) separating an air flow (F) into a primary flow (F1) and a secondary flow (F2); a compressor (14) compressing the primary flow...
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WO/2022/263750A1 |
The invention relates to a system (100) which comprises: a gas turbine (102) designed so that a combustion chamber (110) can be ignited in a first ignition range of rotational speeds of a compressor shaft (112); and a control device (106...
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WO/2022/263203A1 |
The invention relates to an air inlet (1) of an aircraft propulsion unit (8) comprising thrust reversal means configured to modify a bypass air flow circulating from upstream to downstream in a bypass duct (6) into a reverse air flow (F-...
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WO/2022/263307A1 |
A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank, the fuel circuit comprising a buffer tank (R2) for supplying the turbine engine and a plurality of compression modules (1A-1D) co...
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WO/2022/079372A9 |
The present invention relates to a device (8) for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbomachine, in particular of an aircraft, the device (8) comprising a rotating main bod...
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WO/2022/261538A1 |
A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electr...
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WO/2022/260630A1 |
The invention relates to at least one air intake (2) in a cylindrical form extending outwardly from the engine (M) and providing air supply to the engine (M) in air vehicles, an inlet port (3) through which air supply takes place to the ...
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WO/2022/258903A1 |
The invention relates to an aircraft turbine engine assembly (20) comprising: an intermediate housing hub (30); a support (40) for equipment, having an upstream surface (42) located downstream of the intermediate housing hub; and a trans...
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WO/2022/254148A1 |
The invention relates to a turbomachine comprising a rotary body comprising a motor shaft supplying mechanical power, and at least one magnetic drive pump comprising at least: one stator (110) delimiting an annular inner space and compri...
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WO/2022/254141A1 |
The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure 22 having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position ...
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WO/2022/256010A1 |
An inlet shield with a first portion that is configured to be secured to an inlet of a turbocharger, and a second portion that is configured to be removably coupled to the first portion via magnets, wherein different second portions may ...
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WO/2022/247290A1 |
The present invention provides a dual-fuel and multi-fuel internal combustion power device, and relates to thermodynamics and the technical field of thermodynamics. An exterior is provided with low-grade fuel that communicates with a hea...
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WO/2022/248795A1 |
Disclosed is an assembly for supporting a main accessory gearbox (82) of an aircraft turbine engine (10), said accessory gearbox (82) comprising gears and supporting at least one item of equipment (86) driven by the gears, the support as...
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WO/2022/248790A1 |
This acoustic treatment panel (8; 27; 28) for a jet engine (24) comprises a solid skin (9), a perforated skin (10) and an arrangement of cellular structures (11) sandwiched between the solid skin (9) and the perforated skin (10), the cel...
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WO/2022/248798A1 |
A turbomachine comprising a low-pressure shaft (1) extending along an axis (X-X) of the turbomachine which defines a front and a rear; a turbomachine stator (2) supporting the low-pressure shaft by bearings including a rear bearing (3); ...
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WO/2022/248202A1 |
Disclosed is a method of determining an operating condition of a valve of an aircraft system. The method includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the v...
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WO/2022/246424A1 |
The present application provides a spark plug testing tool for a spark plug assembly of a gas turbine engine combustor. The spark plug testing tool may include a dielectric tube attached to the spark plug assembly and a first support bra...
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WO/2022/243622A1 |
A device (110) for guiding a main air flow (F1) for an aircraft turbine engine (22), said device comprising: a first air flowing pipe (112) of a main air flow (F1), said first pipe having a main axis (A), - a plurality of ejectors (114) ...
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WO/2022/246358A1 |
Chilled seawater formed through interaction with a liquefied gas vaporizer may facilitate various types of heat exchange processes. The extent to which the seawater may be cooled is often limited by local environmental regulations for di...
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WO/2022/243457A1 |
The invention relates to a housing (20) of a turbocharger having a cooling system (10). The cooling system (10) comprises a pressure-measuring device (11) for measuring an absolute housing internal pressure (p1) and an absolute coolant p...
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WO/2022/238664A1 |
The invention relates to a propulsion assembly comprising an actuator (40) connected to an outer casing (11) of a turbomachine by a connecting structure (45). The connecting structure (45) is fastened in line with a structural arm (12) c...
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WO/2022/234210A1 |
The invention relates to a transmission device (1) for hybrid aircraft comprising a turboshaft engine having a gas generator (12), a free turbine (14), and a main rotor (52), the device comprising a first reversible electric motor (30) c...
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