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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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WO/2022/234221A1 |
The invention relates to a turbofan (1) having a fan (2), at least one annular casing (11) surrounding said fan, elements (15, 17) being fastened onto an outer surface of the casing via a fastening assembly comprising: a first elastic me...
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WO/2022/228724A1 |
A turbomachinery plant comprises a mechanical hybrid gas turbine and a cooling system for the mechanical hybrid gas turbine conceived to increase/decrease a flow rate of a refrigerant fluid cooled by a chiller (5) so as to an amount of a...
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WO/2022/229556A1 |
The invention relates to a thrust reverser (30) for an aircraft bypass turbojet engine nacelle, this thrust reverser having a generally annular shape around an axis (A) and comprising in particular flaps (10) for deflecting the secondary...
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WO/2022/228723A1 |
A turbomachinery plant is conceived to maximize the power generated by an electrical reversible machine (2) when works as a generator, by reducing the power absorbed by a compressor (3) connected to the electrical reversible machine (2)....
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WO/2022/224871A1 |
This blade ring assembly comprises: a turbine blade ring extending in a circumferential direction about an axis; a component to be cooled, disposed on an inner circumferential side of the turbine blade ring; and an outer circumferential ...
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WO/2022/223907A1 |
The system comprises: - a fuel tank; - a suction pipe that is connected to the tank and is located higher than the tank; - an electric pump (36); - a supply pump configured to be mechanically driven by an accessory gear box and be connec...
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WO/2022/221889A1 |
Internal combustion engine (1 ) comprising: - an intake manifold (3) which can provide gaseous medium to a plurality of piston- cylinder-units - at least one intercooler (10) coupled to the intake manifold (3) - at least one cylinder hea...
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WO/2022/222661A1 |
A hypersonic large internal contraction ratio air inlet channel which has a stepless adjustable air release valve, comprising an air inlet channel front body (1), an air-discharging slit cover plate (2) extending backwards from the air i...
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WO/2022/220002A1 |
A combustion device 10 includes an ammonia tank 14, a combustor 13 connected to the ammonia tank 14, an air supply source 16, and an ammonia autothermal decomposition device 17 that is connected by inlets 17c1 and 17c2 to the ammonia tan...
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WO/2022/219274A1 |
The invention relates to an acoustic panel (12) for a turbine engine, comprising a first strip (20) and a second strip (22) each comprising an alternation of first (20a, 22a) and second (20b, 22b) ridges which are connected by flanks (20...
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WO/2022/219204A1 |
The present invention relates to a multilayer structure with at least one inner layer of alkaline earth silicate mineral wool soluble fibre paper (AES paper) and an outer layer of alkaline earth silicate mineral wool (AES wool), as well ...
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WO/2022/220785A1 |
A process is provided for separating syngas fuel into a CO-rich stream for feeding to oxyfuel combustor means of C02 turbine means and a H2-rich stream for feeding to air-fuel gas turbine means for generating power provides opportunity t...
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WO/2022/214757A1 |
The invention relates to a turbomachine comprising a gas generator (13) equipped with a first shaft (18), an accessories box (14), at least one reversible electrical machine (11) coupled with the accessories box (14), a free turbine (12)...
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WO/2022/216779A1 |
A power generation system includes a reactor operable to produce a flow of hydrogen and a flow of steam in response to the receipt of a flow of reactant mixture. A combustor is operable to produce a flow of combustion gas in response to ...
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WO/2022/213688A1 |
The present invention provides a hydrogen fuel-low-grade fuel combined cycle power device, which relates to the technical field of dual-fuel combined cycle power. A low-grade fuel channel is provided outside to be in communication with a...
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WO/2022/212059A1 |
Embodiments of a fuel system are disclosed. The fuel system includes a bypass valve (BPV), a fuel metering valve (FMV), a flow sense valve (FSV), and an actuator regulating valve (ARV). The BPV includes a BPV valve member that regulates ...
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WO/2022/208801A1 |
This fan case assembly for a turbofan engine comprises: a cylindrical fan case that surrounds a fan of the turbofan engine from the outside in the radial direction; a cylindrical panel set that covers the inner circumferential surface of...
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WO/2022/209562A1 |
A gas turbine system 1 is provided with: an ammonia tank 14; a combustor 13 that is connected to the ammonia tank 14 and that has a combustion chamber 13a; a suction flow channel 41 that is connected to the combustor 13; a compressor 11a...
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WO/2022/208861A1 |
A heat-resistant alloy member comprising: a heat-resistant alloy substrate; Re-based, W-based, or Cr-based multipurpose alloy layer provided on the surface thereof in a region that comprises at least a region where thermal insulation sho...
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WO/2022/209993A1 |
A combustor according to the present disclosure includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which tube plate is formed an air hole passing through the...
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WO/2022/212527A2 |
Filter elements, filter mounting systems, filter systems, methods of servicing filter systems, and methods of mounting filter elements are provided herein. The mounting system may include a quick attach attachment member that can be both...
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WO/2022/212321A1 |
Leveraging a turboexpander to provide additional functionality in compressed gas fueled systems is disclosed. The system includes a compressed gas storage device storing a compressed gas at a first pressure. A turboexpander operably coup...
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WO/2022/209563A1 |
A gas turbine system 1 comprising: an ammonia tank 14; a combustor 13 connected to the ammonia tank 14; an exhaust flow path 42 connected to the combustor 13; a turbine 11b provided in the exhaust flow path 42; a decomposed gas reservoir...
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WO/2022/198780A1 |
Provided are a purging system (200) for a turbine fracturing device group and a turbine fracturing device group comprising the purging system (200), and also provided is a purging method of the purging system (200). The turbine fracturin...
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WO/2022/200729A1 |
The present invention relates to an upstream part of an air evacuation system for a turbomachine. The upstream part comprises a tube with an upstream end and a downstream end, an inner tubular structure situated inside said tube and conf...
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WO/2022/202869A1 |
In this gas turbine system, and a method for controlling the same, provided with a gas turbine comprising a compressor for generating compressed air, a combustor for burning fuel with the compressed air, a turbine which is driven by mean...
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WO/2022/202510A1 |
A stationary blade assembly of a gas turbine comprising: a stationary member formed in an annular shape, and a plurality of stationary blade segments each provided with a shroud and a blade body, the stationary blade segments being arran...
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WO/2022/201932A1 |
This turbine comprises a turbine rotor, a turbine casing, a plurality of turbine rotor cascades, a plurality of turbine stator cascades, and a diffuser which forms an exhaust gas flow path through which exhaust gas flows from one side in...
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WO/2022/198273A1 |
A combined energy storage and power production system (200) comprises: a hydrogen and oxygen production unit (100); a hydrogen compression, cooling and storage unit (200A) for compressing, cooling and storing hydrogen from the hydrogen a...
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WO/2022/195193A1 |
The invention relates to a device for centring and guiding a shaft of an aircraft turbine engine, said device comprising: – an outer ring (12) of a rolling bearing, said ring extending about an axis (X); – an annular bearing support ...
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WO/2022/195224A1 |
The invention relates to a system (400) for pumping and metering a fluid (10) for a turbine engine, which system comprises at least one pump (412, 414) for the fluid and an electronic computer (430) configured to determine the flow rate ...
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WO/2022/195198A1 |
Disclosed is a device for centring and guiding a shaft of an aircraft turbine engine, said device comprising: an outer ring (12) of a rolling bearing (14), extending about an axis and comprising orifices (42a, 42b), an annular bearing su...
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WO/2022/195194A1 |
The invention relates to a device for centring and guiding a shaft of an aircraft turbine engine, said device comprising: - an outer ring (12) of a rolling bearing (14), said ring extending about a main axis (X) and having orifices (42a,...
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WO/2022/195191A1 |
The invention relates to a fan module for an aircraft turbine engine, this module comprising a fan (12) comprising variable pitch blades (12a) and an oil transfer device (174) configured to provide a transfer of oil between a stator and ...
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WO/2022/190689A1 |
Provided is a seal member which forms a combustion gas flow path of a gas turbine, wherein: the seal member includes a first main body part having therein a cooling path; the first main body part comprises a first end section which forms...
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WO/2022/189153A1 |
The invention relates to an accessory gearbox (2) for an aircraft turbine engine comprising a radial shaft connecting the high-pressure body of the turbine engine to a gear train (22) comprising at least one mixed shaft (25) coupled to a...
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WO/2022/189712A1 |
The invention relates to a turbomachine device of the intercooled recuperated reheated gas turbine (IRReGT) type. The invention relates to applications for motor vehicles. The turbomachine device comprises a first turbocompressor (C1, T2...
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WO/2022/190080A1 |
Turbine apparatus includes turbine wheels by which introduced motive fluid is expanded; a horizontally disposed turbine shaft which is rotatably supported by inlet-side and outlet-side bearings, such that the turbine wheels are fixedly c...
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WO/2022/189898A1 |
An aircraft (1) capable of hovering is described, comprising a motor member (10); a rotor (5) connected to the motor member (10); a transmission shaft (11) rotatable around a first axis (B) and adapted to drive the rotor (5); and a trans...
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WO/2022/189154A1 |
Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger...
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WO/2022/189157A1 |
Disclosed is a fuel conditioning system (SC) configured to power an aircraft turbine engine (T) using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one first heat exchanger (31) configured to heat ...
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WO/2022/189739A1 |
The surface heat exchanger (20) for an aircraft turbomachine (1) comprises a support wall (21), a panel (22) arranged substantially parallel to the support wall (21), partitions (23) connecting the wall (21) to the panel (22) that define...
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WO/2022/184902A1 |
A turbocharging assembly (10) is described. The turbocharging assembly (10) includes a compressor (20) having a compressor wheel (21) and a turbine (30) having a turbine wheel (31). The turbine wheel (31) and the compressor wheel (21) ar...
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WO/2022/184530A1 |
An air inlet (1) of a nacelle (2) of an aircraft propulsion assembly (8) comprising an inner wall (11) and an outer wall (12) which are connected upstream by an air inlet lip (13), the air inlet lip (13) comprising thick portions and thi...
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WO/2022/181694A1 |
A cylinder for combustion (20) comprises a barrel (21) that forms a cylindrical shape, and an air supply pipe (40). An insertion opening (25) and a plurality of cooling flow paths (30) are formed in the barrel (21). A part of the air sup...
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WO/2022/180340A1 |
A turbine (1) for a turbomachine of longitudinal axis (X), comprising: an alternating arrangement of annular rows of movable blades (64) and of fixed blades (65) and a radially inner annular cavity (68) formed radially inside the movable...
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WO/2022/180327A1 |
A method for generating an alarm is implemented by an alarm-generating device (10) installed in an aircraft. It comprises: a step (F10) of obtaining information (POS d) delivered by a sensor (18) of said device and representative of an o...
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WO/2022/182730A1 |
A method and system for enhancing power generated by a gas turbine system. The system may include a turbine inlet cooling system and a wet compression air fogging system. Air entering the gas turbine system is cooled by the turbine inlet...
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WO/2022/180311A1 |
The invention relates to a gas turbine cycle-type turbine engine device with cooled compression, regeneration and reheating during expansion. The turbine engine device comprises a first turbocharger (C1, T2), a second turbocharger (C2, T...
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