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WO/2022/182622A1 |
An ignition and combustion assist system and method comprising a plasma igniter and electronic driver unit for use with gas turbine engines operating under low air densities, reduced voltage conditions and overall pressure ratios of 3:1 ...
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WO/2022/176805A1 |
A turbine blade and a rotating machine, wherein provided are: a blade (31); a hollow section (41) that is provided in the blade (31); and a low-melting-point metal (42) that is filled into the hollow section (41).
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WO/2022/175087A1 |
A method, a device and a control unit for establishing or for releasing a press fit between at least one first component (42) and at least one second component (34) and at least one wedge sleeve (43) arranged in between are described. Du...
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WO/2022/178521A1 |
A vibration damper (100) for a fuel conduit (40) of a gas turbine combustor includes a mounting portion (102) and a damping portion (104). The mounting portion (102) is secured to the fuel conduit (40), and the damping portion (104) incl...
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WO/2022/176302A1 |
This premixed combustion burner comprises: an outer tube that has an inlet opening on the first side in the axial direction in which the axis extends and an outlet opening on the second side in the axial direction; an inner tube that is ...
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WO/2022/175088A1 |
The invention describes a method and a controller for fitting a rotationally operable device with a plurality of components (32 to 43). The individual components (32 to 43) are identified with a machine-readable data set before being fit...
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WO/2022/173040A1 |
This gas turbine plant is provided with a gas turbine and a fuel supply facility. The fuel supply facility is provided with: a liquid ammonia line; a warm water line through which warm water can flow; a vaporizer which can perform the he...
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WO/2022/172955A1 |
This fuel supply equipment comprises: a main ammonia line through which liquid ammonia flows; a vaporizer which is connected to an end of the main ammonia line, and which performs heat exchange between a heating medium and the liquid amm...
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WO/2022/171451A1 |
The present invention relates to a combustion system with a tubular combustion chamber (5) and an annular counter-flow heat exchanger (4) around the combustion chamber (5).
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WO/2022/172853A1 |
This gas turbine equipment comprises a gas turbine and a control device. A combustor of the gas turbine uses ammonia as fuel, and uses the RQL method. A compressor of the gas turbine includes an intake adjustor that adjusts an intake rat...
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WO/2022/171366A1 |
A turbomachinery installation (1) for an offshore platform is disclosed. The turbomachinery installation comprises a train system (2) having at least one preassembled power module (20), and a torque tube baseplate (3), on which the train...
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WO/2022/167742A1 |
Discharge valve (48) of an aircraft turbomachine (10), comprising a discharge gate (50) intended to be mounted pivotably about an axis (51) between a position for closing an air passage orifice (60) and an open position of said orifice, ...
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WO/2022/160543A1 |
A fracturing device (5), comprising a noise reduction chamber (11), a turbine engine (12), an air inlet apparatus (13), and a cleaning apparatus (14). The air inlet apparatus (13) is communicated with the turbine engine (12) by means of ...
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WO/2022/163030A1 |
A turbine stator vane (24) comprising a vane body (40) and a shroud (60) formed at an end part of the vane body in a vane height direction, wherein the shroud comprises: a bottom plate (82) in contact with a combustion gas flow path; a c...
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WO/2022/157443A1 |
Assembly comprising an aircraft turbine engine (10) and a pylon (32) for mounting the turbine engine to an element of the aircraft, the pylon comprising members (34, 36) for suspending the turbine engine (10), said members being connecte...
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WO/2022/156925A1 |
The invention is about a combustion section (01) of a gas turbine (02) comprising an annular combustion chamber (07), and a burner arrangement (08) upstream of the combustion chamber (07), and an annular compressor diffusor (15), and an ...
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WO/2022/152994A1 |
The invention relates to a propulsion assembly (200) for an aircraft comprising a double-flow turbomachine (1) equipped with a fan (15), an aerodynamic outer casing (5) forming a nacelle, and a mounting pylon, the propulsion assembly hav...
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WO/2022/152621A1 |
A system (S) for supplying fuel (C) to the combustion chamber (5) in an aircraft turbine engine (6), comprising injectors (1) comprising a first pilot stage (10), a second pilot stage (16) and a main stage (13), the pilot stages (10, 16)...
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WO/2022/153000A1 |
The invention relates to a turbomachine fan module (10) comprising a fan shaft (5) and a lubrication chamber (8) traversed axially by at least part of the fan shaft and comprising at least one first bearing (6, 7) intended to support and...
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WO/2022/152989A1 |
Ignition method for a continuous combustion engine comprising an electronic engine control member (7), a high-power housing (2), a spark plug ignition circuit and a solenoid fuel valve engaging with a starter, the method being implemente...
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WO/2022/154808A1 |
The present invention is a safety shield to be secured with nacelle of aircraft. The safety shield is shaped for a nacelle such that the nacelle is covered by use of safety shield. Additionally, the shield frame of the safety shield is p...
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WO/2022/149540A1 |
A gas turbine combustor according to at least one embodiment of the present invention comprises: a low combustible fuel flow adjuster for independently adjusting the amounts of low combustible fuel to be supplied to a first fuel injector...
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WO/2022/144236A1 |
An air inlet (5) for an aircraft propulsion unit (8) comprising a movable upstream portion (1), a stationary downstream portion (2) and at least one member (3) for longitudinally translating the movable upstream portion (1) between a ret...
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WO/2022/144514A1 |
The invention relates to an aircraft turbomachine module, comprising an accessory gearbox (30) as well as a transfer shaft (34) and a drive shaft (25) rotatably connected with one another by means of a power transmission device (37), the...
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WO/2022/139054A1 |
According to one aspect of the present invention, provided is a device for opening an intake port of a ramjet engine, the device comprising: a duct part having an intake port; a shutter part for covering the intake port when the intake p...
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WO/2022/134200A1 |
The present invention relates to the technical fields of thermomechanics and thermodynamics, and provides a dual-fuel gas turbine apparatus. A low-quality fuel communicated with an air heating furnace is provided at the outside of the ap...
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WO/2022/127054A1 |
A micro gas turbine having an axial force balancing structure, the micro gas turbine comprising a rotating shaft (24), an air compressor (20), a turbine (21) and a combustion chamber (231), wherein the air compressor (20) and the turbine...
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WO/2022/129785A1 |
Disclosed is a plate heat exchanger (1), in particular for an aircraft turbomachine, between a first fluid and a second fluid, the first fluid being intended to circulate in a first direction (X) and the second fluid being intended to ci...
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WO/2022/129788A1 |
Aircraft turbine engine assembly (20), comprising an intermediate housing hub (30), a holder (40) for fittings and a transfer case (50) comprising a power transmission shaft (54) configured to transmit mechanical power, taken from a driv...
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WO/2022/126248A1 |
An improved power generation system for aircraft and methods of its operation are provided, wherein the system combines a wave reformer providing a contiguous fuel supply to a jet engine, and use of ammonia as the fuel source from which ...
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WO/2022/129778A1 |
Disclosed is an acoustic treatment panel comprising acoustic absorption cells (18) each comprising a bottom wall (180), a porous inlet wall (181), an enclosure (185) extending in an axial direction (DA) between the bottom wall (180) and ...
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WO/2022/129756A1 |
The invention relates to a propulsion unit (1) for an aircraft, this propulsion unit (1) comprising: - a gas generator (3), and - an air intake (2) comprising an upstream annular lip (10) that is axially translatable, and - a sealing sys...
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WO/2022/123151A1 |
The invention relates to a turbine engine (1) extending along an axis (X), comprising a flow path (2) of a primary flow (F1) comprising a compressor, a combustion chamber and a turbine, an outflow region (3) of a secondary flow (F2), sur...
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WO/2022/123830A1 |
Provided is a turbine component production method, and the like, with which it is possible to obtain a single-crystal structure more simply and produce a favorable turbine component. In a seed crystal placement step, a seed crystal is pl...
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WO/2022/121267A1 |
A gas turbine fault monitoring system and method. The system comprises a detection module (101), a fault level determining module (102), a control module (103), and a fault response execution module (104). The detection module (101) dete...
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WO/2022/123160A1 |
One aspect of the invention relates to an oil jet (200) for lubricating members such as bearings inside a turbine engine, comprising: - a main pipe (210) for supplying oil, - at least one secondary oil discharge pipe (220) through which ...
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WO/2022/123168A1 |
The invention relates to a heat exchange system (20) for a turbine engine, comprising: - a cavity (22) comprising an air intake (23), - a heat exchanger (21) arranged in the cavity and comprising a first circuit (26) in which a first flu...
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WO/2022/123100A1 |
Disclosed is a protective device for aeroplane engines that prevents birds and other foreign objects from entering the engines. The device comprises a metal rod structure in the form of a grille that covers the opening of the engine air ...
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WO/2022/122113A1 |
The present invention relates to a rotary catalytic converter, a method for operating the rotary catalytic converter, an apparatus and a method for converting chemical energy into electrical energy, and the use of the rotary catalytic co...
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WO/2022/121266A1 |
A gas turbine energy storage system and a peak-valley power generation mode. The gas turbine energy storage system comprises a core machine and a free machine. The core machine comprises a gas compressor (102), a turbine (104), and a com...
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WO/2022/123146A1 |
Disclosed is a propulsion unit (100) for an aircraft, this propulsion unit comprising: - a gas generator (102); - an air inlet (110); and - a sealing system (112) inserted axially between the air inlet and the gas generator, characterise...
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WO/2022/117968A1 |
A multicellular acoustic-attenuation panel (220) comprises several rows of acoustic cells (240, 250, 260, 270, 280) each extending in a circumferential direction (DC), each acoustic cell being delimited by a wall (241, 251, 261, 271, 281...
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WO/2022/117465A1 |
A method of controlling a combustor of a gas turbine engine, the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fu...
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WO/2022/117464A1 |
A method of controlling a combustor of a gas turbine engine is disclosed. The method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split in...
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WO/2022/117812A1 |
Said method is implemented via a power generation unit (14) comprising at least one combustion turbine (16) configured to generate, at defined site conditions, without cooling or heating the incoming air stream (20), a defined site elect...
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WO/2022/117947A1 |
The invention relates to an aircraft turbine engine assembly, comprising a lubricating oil circuit (1') and a fuel supply device (1), the assembly also comprising a passive bypass valve (20) enabling the oil to bypass an exchanger (7), t...
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WO/2022/117406A1 |
The present invention relates to a compressed gas energy storage and recovery system comprising: - a gas compression line (1) with a compression stage (3) comprising a compression means (100, 101, 102) and a means for storing and recover...
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WO/2022/117932A1 |
The invention relates to a power transmission system for an aircraft turbine engine comprising a speed reducer (32) comprising a ring gear (40) that is able to rotate about an axis X, formed from half-rings (40a, 40b) having annular flan...
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WO/2022/118872A1 |
A load adjustment method that includes a step for acquiring a warm-up parameter that indicates the degree to which a gas turbine that is operating under a load has warmed up, a step for determining an upper limit for a rate of load incre...
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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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