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WO/2023/213852A1 |
The invention relates to a turbomachine comprising a heat exchanger (11), a first circuit (13) for a first fluid, the first circuit (13) comprising two pipes (31, 33) in the heat exchanger (11), a second circuit (15) for a second fluid a...
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WO/2023/214507A1 |
A plurality of circumferentially-arranged split plates retained by a seal-ring retention ring include a plurality of first split-plate groups that are circumferentially arranged on one circumferential side of the seal-ring retention ring...
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WO/2023/209297A1 |
The invention relates to a method for controlling a two-stage gas cycle thermodynamic system, the method successively comprising: - a step of activating an electric machine (EMG2) until a respective minimum engine speed is reached for ea...
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WO/2023/209291A1 |
Accessory gearbox (50) for an aircraft turbine engine, comprising:• - a casing (52), • a reduction gear (62) and a freewheel (62) which are permanently integrated into the casing, the accessory gearbox being configured to interface w...
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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/2023/208872A1 |
The invention relates to a system (1) for controlling the temperature of a heat transfer fluid (F) configured to transfer heat to a fluid to be heated (Q) originating from a cryogenic tank (R), the control system (1) comprising: a loop (...
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WO/2023/211473A1 |
A system for providing mobile electric power includes a first transport including an inlet plenum and a generator, a second transport including a gas turbine, and a turbine exhaust unit, and a third transport including a generator exhaus...
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WO/2023/208884A1 |
The invention relates to a conditioning system (SC) for fuel (Q), which is configured to supply an aircraft turbine engine (M) with fuel (Q) from a cryogenic tank (R), the conditioning system (SC) comprising at least one first heat excha...
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WO/2023/210226A1 |
This combustor attachment jig is a jig for attaching a combustion cylinder of a combustor to a gas turbine, and comprises a fixed portion capable of being fixed to a combustor insertion hole portion of a casing of the gas turbine, and an...
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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/2023/211278A1 |
An aircraft powerplant includes an engine having an output power shaft. The aircraft powerplant further includes a power transmission coupled to the output power shaft of the engine. The power transmission is configured to divide power o...
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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/2023/203131A1 |
A compressor-expander system (10) having a compressor (12) that can be driven by an electric machine (11), in order to take in air to be compressed from an environment, having a first heat exchanger (13) arranged downstream of the compre...
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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/2023/204096A1 |
A gas turbine control device of the present disclosure controls a gas turbine in which a combustor is configured in a state where a plurality of fuel supply nozzles for supplying fuel are separated into a first group and a second group. ...
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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/2023/199725A1 |
This method for constructing a thermal barrier coating according to at least one embodiment of the present disclosure comprises a step for forming a topcoat layer on a bond coat layer formed on a heat-resistant alloy base material of a t...
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WO/2023/200314A1 |
A fuel supply system according to the present invention vaporizes mixed fuel supplied to a power generation system. The fuel supply system comprises: a condenser for condensing steam conveyed from a turbine of the power generation system...
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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/2023/194692A1 |
The invention relates to a method for manufacturing a rotationally symmetrical part made of composite material (100) for a propulsion assembly comprising: - manufacturing a fibre preform on a mandrel (200) having a profile corresponding ...
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WO/2023/196129A1 |
A method of monitoring behavior of a device includes obtaining, at a computing device, first data based on first sensor data from a first sensor device coupled to the device. The method includes processing, at the computing device, the f...
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WO/2023/186731A1 |
The invention relates to an accessory gearbox (124) of an aircraft engine (1), said accessory gearbox comprising a gearbox housing (23), at least one gearbox input shaft (22), and at least one gearbox output shaft (31). The gearbox input...
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WO/2023/188984A1 |
This combustor comprises a combustor plate which has a downstream end face perpendicular to the combustor axis, a nozzle segment in which a plurality of first nozzles for injecting a premixed gas of air and fuel from the downstream end f...
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WO/2023/184657A1 |
Provided in the present application is a connection structure for connecting a first workpiece to a second workpiece. The connection structure comprises a first connection assembly arranged on the first workpiece; a second connection ass...
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WO/2023/188749A1 |
This combustor comprises: a combustor plate that has a mixing tube which extends so as to penetrate the combustor plate upstream end face and downstream end face perpendicular to the combustor axis and into which air is introduced from t...
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WO/2023/179824A2 |
The present invention relates to a jet burner apparatus (100) for combusting at least one fuel with at least one oxidising agent, wherein the jet burner apparatus (100) comprises a central longitudinal axis (102) and a main flow directio...
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WO/2023/181512A1 |
A combustion system 1 comprises an ammonia tank 14, a combustor 12 connected to the ammonia tank 14, an intake flow path 101 connected to the combustor 12, a compressor 11a provided in the intake flow path 101, an ammonia recovery tub 16...
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WO/2023/181616A1 |
A device for controlling gas turbine equipment comprises: a combustion load command generator that determines a combustion load command value, which is a parameter having a positive correlation with an inlet temperature, which is the tem...
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WO/2023/179911A1 |
A firing apparatus to control the firing of one or more burners of a gas turbine is disclosed. The firing apparatus comprises a shutoff module, for selectively allowing the passage of the fuel from a fuel source, and an adjustment module...
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WO/2023/176050A1 |
A gas turbine system (1) comprises: an ammonia tank (13) that stores ammonia; a combustor (12) connected to the ammonia tank (13); an exhaust flow passage (102) connected to the combustor (12); a boiler (14) provided in the exhaust flow ...
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WO/2023/175254A1 |
The invention relates to a turbomachine (100) for a hybrid aircraft, the turbomachine comprising a gas generator (12) carried by a generator shaft (14), at least one free turbine (11) carried by a turbine shaft (13) and rotated by a gas ...
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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/2023/176577A1 |
A method for applying a thermal barrier coating according to one embodiment includes a step for forming a topcoat layer on a bond coat layer formed on a heat-resistant alloy substrate of an object. In the step for forming the topcoat lay...
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WO/2023/175282A1 |
The invention relates to an aircraft turbomachine (10) comprising: a gas generator (12) comprising an output shaft (26) as well as a first lubricating circuit (28); and equipment (14) coupled to the output shaft (26) and comprising a rot...
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WO/2023/175261A1 |
Aeronautical device 1 for distributing gas in an aircraft between at least one source 2 of liquefied gas and at least one gas consumer member 3, comprising at least one first controlled all-or-nothing valve 11 at the output of each sourc...
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WO/2023/175270A1 |
The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises a gas turbine engine (200) and at least one electric machine (300, 400) which is mechanically coupled to a rotating shaf...
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WO/2023/171752A1 |
Provided is a method for cooling a turbine stationary blade. A turbine comprises: an airfoil; and an outer shroud and an inner shroud that are provided on a radial outer edge of the airfoil. The airfoil comprises a plurality of air chann...
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WO/2023/168777A1 |
The present application discloses a gas turbine generator set and mobile power generation equipment. The gas turbine generator set comprises a gas turbine, a generator and an equipment cabin. The gas turbine is arranged in the equipment ...
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WO/2023/170357A1 |
The invention relates to an aeronautical propulsion unit (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), wh...
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WO/2023/171048A1 |
A gas turbine system (1) comprises: an ammonia tank (13) in which ammonia is stored in a liquid state; a combustor (12) which is connected to the ammonia tank (13) and to which ammonia is supplied in a liquid state; an exhaust channel (1...
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WO/2023/171745A1 |
The present disclosure provides a method for cooling static vanes of a turbine. The turbine comprises airfoils and a shroud arranged at radial end portions which are end portions of the airfoils along the radial direction of the turbine....
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WO/2023/166266A1 |
The present document relates to an exhaust cone for an aircraft turbine engine, extending along a longitudinal axis (X), said cone comprising a radially inner annular wall (104) and a radially outer skin (102) delimiting a flow path for ...
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WO/2023/166273A1 |
A device (20) for supporting a fluid duct (C), comprising: - a link (22) for supporting the duct via two end parts (22a) of the link that are spaced apart from one another in a longitudinal direction and adopting, transversely, a curved ...
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WO/2023/166534A1 |
Think above the speed of sound and engineering which breaks that barrier of sound speed and gives us supersonic and hypersonic speeds many cruise missiles and air-to-air missiles work on supersonic speed mostly between Mach 2.5 to Mach 4...
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WO/2023/166256A1 |
A propulsive assembly (100) for a multi-engine hybrid aircraft, comprising a first and a second gas turbine (10, 20) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21)...
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WO/2023/161586A1 |
The present invention relates to an aircraft engine assembly comprising: a duct (4); a beam (51); and an acoustic fairing.
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WO/2023/162589A1 |
This gas turbine plant comprises: a waste heat recovery boiler; an ammonia vaporizer that produces gaseous ammonia by causing heat to be exchanged between steam from the waste heat recovery boiler and liquid ammonia; an ammonia heater th...
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