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WO/2023/091583A1 |
An enclosure for an aircraft powerplant includes an air inlet, an air outlet, and at least one sidewall forming the enclosure and fluidly connecting the air inlet and the air outlet. The enclosure further includes a cavity configured to ...
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WO/2023/084176A1 |
The invention relates to a method (300) for manufacturing a metal protection device (120) for a leading edge (130) of a blade made of composite material for a turbojet engine, comprising the operations of: - a) shaping (310) a pressure-s...
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WO/2023/083490A1 |
A method of controlling the renewable energy absorbed by a hybrid power train (2) for driving a load, and in particular compressors for a liquefied natural gas (LNG) plant is disclosed. The method comprises an analysis of the health stat...
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WO/2023/082481A1 |
A system and method for supplying combustion gas, a device equipped with a turbine engine, and a fracturing system. The combustion gas supply system comprises a main pipeline and a multifunctional pipeline, wherein the main pipeline comp...
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WO/2023/083494A1 |
A power plant for controlling the renewable energy absorbed by a hybrid power train (2) for driving a load, and in particular compressors for a liquefied natural gas (LNG), is disclosed. The power plant analyses the health status of it p...
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WO/2023/079233A1 |
The invention relates to an acoustic attenuation structure (100) comprising a lower multicellular structure (130) and an upper multicellular structure (110), at least some of the cells (112) of the upper multicellular structure (110) at ...
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WO/2023/079217A1 |
The invention relates to a system (2) for detecting leaks from an aircraft engine, comprising: - a tank (10) having an outlet opening (18); - a piping system (12) comprising a main pipe (20) having a first portion (22) of pipe connected ...
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WO/2023/081162A1 |
In general, the present invention is directed to methods for enhancing or improving the performance of a gas turbine. Generally, the present invention provides a method for adding additional air directly to a specific area within the com...
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WO/2023/081922A1 |
A system and method for controlling a hydraulic fracturing pumping system is described herein. The method can include stopping an engine coupled to a hydraulic fracturing pumping system including at least one pump by supplying pressure f...
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WO/2023/073305A1 |
Turbomachine (100) comprising a fan (120) arranged along a longitudinal axis (X) of the turbomachine, a primary duct (130) able to channel a primary air flow of the fan through a compressor, a combustion chamber and a turbine of the turb...
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WO/2023/072614A1 |
The invention relates to a fuel conditioning system (SC) configured to supply a turbomachine (T) with fuel (Q) from a cryogenic tank (RI), the conditioning system (SC) comprising a fuel circuit (CQ) connected at the inlet to the cryogeni...
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WO/2023/072623A1 |
The invention relates to a fuel conditioning system (SC) configured to supply an aircraft turbomachine (T) with fuel (Q) from a cryogenic tank (RI), the conditioning system (SC) comprising a primary heat exchanger (EX1) designed to heat ...
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WO/2023/073302A1 |
In order to detect possible leaks of fuel into oil used in an aircraft engine when their circuits are connected via a heat exchanger liable to deteriorate, a gauge (22) measuring the liquid level in a tank (2) in which the oil is stored,...
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WO/2023/072344A1 |
The invention relates to an aircraft engine for commercial aircraft. The problem to be solved by the invention is that of providing an aircraft engine having a fuel-cell-based, electrically operated axial-flow fan which, according to the...
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WO/2023/074866A1 |
This fuel supply system (1) for a hydrogen aircraft comprises: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges liquefied hydrogen from the fuel tank (2) and supplies the same to a propulsion device (102); a pre...
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WO/2023/073306A1 |
A method for detecting the presence of a crosswind for a turbomachine of an aircraft comprising at least two turbomachines arranged on either side of a main axis of the aircraft, each of said turbomachines comprising a low-pressure shaft...
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WO/2023/065377A1 |
The present invention relates to the field of new concept unsteady combustion. Disclosed are an isolated section shock wave forward propagation suppression structure for an internal combustion wave rotor, and an internal combustion wave ...
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WO/2023/066518A1 |
Expander-compressor system (1000) comprising an expander (700), a compressor (900) and a shaft (800) located in a casing (600) which mechanically couples the expander (700) and the compressor (900); the expander-compressor system (100) c...
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WO/2023/067266A1 |
Device for de-icing an aerodynamic profile (100), comprising a surface referred to as a lower surface, a plurality of unitary cavities (2a, 2b) delimited by a lattice of partitions (3a, 3b) on the surface, and a barrier arranged on the l...
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WO/2023/065851A1 |
A gas turbine, comprising a rotating shaft (10), a gas compressor (20), a combustion chamber (40) and a turbine (30), wherein the gas compressor and the turbine are mounted on the rotating shaft; a gas output end of the gas compressor is...
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WO/2023/064679A1 |
An aircraft (20, 22) propulsion system includes an engine. The propulsion system further includes an inlet (36) having a forward cowl lip (38, 3, 40) and an aft cowl lip (40). The forward cowl lip (38, 3, 40) moves between retracted and ...
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WO/2023/059560A1 |
System designed to compensate for flow disturbances when changing a flow rate in the system, the system including a flow source device (12) having an inlet and an outlet. The inlet is configured to receive fluid at a first pressure, and ...
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WO/2023/052719A1 |
The invention relates to a turbine engine (1, T, 1") including an oil supply system (14) that comprises: a main oil tank (15), a supply pump (18) comprising an inlet (18a) and an outlet (18b) connected to a control system (13), an auxili...
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WO/2023/052718A1 |
The invention relates to an auxiliary supply device (14) that comprises: an auxiliary oil tank (20), an auxiliary pump (22) comprising an inlet (22a) connected to the auxiliary tank (20) and an outlet (22b), a valve (21) comprising a bod...
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WO/2023/051157A1 |
A gas path system for a rotor system of a micro fuel-gas turbine, a micro fuel-gas turbine having the gas path system, and a control method for using the gas path system to realize automatic static-pressure gas supplementation. The rotor...
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WO/2023/051159A1 |
A gas path system for a gas bearing (100). The gas path system comprises a gas source gas path (A), a gas supply gas path (B), a bearing gas path (C) and a buffer tank (200), wherein an input end of the bearing gas path (C) is in communi...
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WO/2023/047841A1 |
This equipment performance evaluation device comprises: an overall performance function acquisition unit configured to obtain an overall performance function indicating a change in the performance index of equipment to be evaluated over ...
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WO/2023/049674A1 |
A method of generating electrical power includes expanding a flow of exhaust gas from a combustion process as the exhaust gas passes through a turbo-expander disposed on a turbo-crankshaft. The flow of exhaust gas from the turbo-expander...
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WO/2023/047043A1 |
The present invention relates to an aircraft turbine engine (1) comprising a dihydrogen control assembly (10) having at least one dihydrogen retention zone (V) in which dihydrogen accumulates. The assembly comprises at least one spark pl...
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WO/2023/044572A1 |
An assembly may include a rim-rotor turbine having a hub adapted to be mounted or connected to a rotating shaft, a rim-rotor, the rim-rotor having a cooling ring defining at least one cooling channel, and a plurality of blades with each ...
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WO/2023/047055A1 |
The present invention relates to a cooling-air injection casing (2) for cooling a bladed rotor disc of a turbine, in particular a high-pressure turbine, of a turbomachine, this casing extending around a longitudinal axis (X-X') and being...
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WO/2023/046632A1 |
In a Ducted fan engine (1), configured for providing thrust for an aircraft (too), in particular an aircraft (100) having vertical takeoff and landing capability, comprising a fan stator (3) having one or more substantially radially exte...
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WO/2023/037075A1 |
Disclosed is an assembly for a turbomachine, comprising: • - a first connection element (9) having a first radial compliance (SRI); • - a second connection element (10) having a second radial compliance (SR2); • - a third connectio...
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WO/2023/037643A1 |
This ammonia fuel combustion device in which ammonia gas NH3 supplied through an ammonia supply pipe 11 and combustion air Air supplied through an air supply pipe 12 are mixed in a combustion burner 10 and combusted in a furnace 1, where...
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WO/2023/038623A1 |
A cyclonic particle separator may include a housing including a cylindrical sidewall having a plurality of flow entry ports. A cover member closes a first end of the cylindrical sidewall, and a mounting member having a flow exit opening ...
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WO/2023/037074A1 |
Disclosed is an assembly for a turbomachine comprising: • - a second connection element (8) having a third end (81) which is connected to a turbine shaft (2) and is mounted on a second bearing (5), and a fourth end (82) connected to a ...
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WO/2023/038622A1 |
A cyclonic particle separator may include a housing including a cylindrical sidewall having a plurality of flow entry ports. A cover member closes a first end of the cylindrical sidewall, and a mounting member having a flow exit opening ...
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WO/2023/036721A1 |
The present invention relates to shrouded fan engine having an acoustic liner (10) for damping sound waves, comprising a base portion (14) on one side of the acoustic liner (10), wherein the base portion (14) is adapted to attach the aco...
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WO/2023/031550A1 |
The invention relates to a method for manufacturing an acoustic panel (20) comprising a first skin (21), a second skin (22) and an intermediate structure (23) enclosed between these skins (21, 22) and forming oblique cavities (31) with r...
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WO/2023/034577A2 |
Microfabricated multiemitter electrospray thrusters in accordance with embodiments of the invention are disclosed. In one embodiment, an electrospray thruster for electrospraying at least one liquid propellant is provided, the electrospr...
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WO/2023/030867A1 |
The invention relates to a drive system (100) for a vehicle, in particular for a hybrid vehicle, with at least one power unit (110) and at least one drive battery (91), which are electrically coupled to one another, wherein the power uni...
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WO/2023/031736A1 |
A turbomachine with a cantilevered rotor wheel for industrial power plants comprises a fixed case (3), a main shaft (10) mounted in the fixed case (3) and carrying a bladed rotor wheel (2), a main pinion (20) on the main shaft (10). A ge...
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WO/2023/027116A1 |
A combustor panel according to the present disclosure comprises: a first panel; a second panel that is disposed to face the first panel, defines a channel for circulating cooling air between the first panel and the second panel, and has ...
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WO/2023/025664A1 |
A system (1) for cooling a refrigerant (R) for an aircraft comprising a plurality of ducts (2) for circulating the refrigerant (R) that are configured to be at least partially in contact with an airflow (A) so as to cool the refrigerant ...
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WO/2023/022641A1 |
A gas turbine power generation plant (100; 200; 300; 400; 500; 600) comprising: a gasifier (102) for producing a fuel gas stream (104); a treatment arrangement (110) for treating the fuel gas of the fuel gas stream (104); a combustor (11...
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WO/2023/018724A1 |
The present invention is directed to a metering valve for controlling the amount of a fluid passed through the valve and a servo-valve for controlling the metering valve, wherein the servo-valve is decoupled from the metering valve to th...
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WO/2023/011762A1 |
In the LNG plant, heat is provided to natural a gas processing system, including a pre-treatment unit and/or a liquefaction unit and/or an evaporation unit, by exploiting heat recovered through a steam generator of the plant that is ther...
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WO/2023/011763A1 |
The disclosure concerns a method for estimating and setting the exhaust purge time in a combustion system comprising a gas turbine, which is configured for estimating whether a purge cycle is needed or not, based on values collected by p...
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WO/2023/011689A1 |
The invention relates to a supply device (10) and to a method (100) for supplying an air bearing (11) by means of a fuel cell system (12), which comprises at least one anode (14) and at least one cathode (15) and a process gas device (17...
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WO/2023/012419A1 |
The invention relates to a bypass turbomachine comprising an exhaust casing (13) traversed by a hot primary flow (FP) and surrounded by a cold secondary flow (FS), and a cone (14) borne by this exhaust casing (13), this exhaust casing (1...
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