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WO/2024/078930A1 |
A fuel conditioning system (SC) configured to supply an aircraft turbine engine with fuel (Q) coming from a cryogenic tank (R), the conditioning system (SC) comprising: a fuel circuit (1); a first heat module (31) mounted in an aircraft ...
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WO/2023/245221A3 |
The present invention relates to a synthesis system (10), a fuel cell system (20), a fuel cell plant (30) including a fuel cell system (20) and a synthesis system (10), and to a process (1000) for producing synthesis gas using the fuel c...
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WO/2024/080334A1 |
A blade ring assembly according to the present disclosure comprises a turbine blade ring extending in a circumferential direction about an axis, stationary blades disposed on the inner-circumferential side of the turbine blade ring, and ...
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WO/2024/075569A1 |
This intermediate shaft cover comprises: a cylindrical inner cover covering an intermediate rotor shaft; an annular outer cover which covers an outer peripheral side of a diffuser space and which is connected to a gas turbine casing; and...
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WO/2024/075568A1 |
A lower half inner casing has a lower half inner casing body forming a semi-circular arc, and an inner casing accessory part provided to the lower half inner casing body. The inner casing accessory part has a protrusion which protrudes r...
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WO/2024/074448A1 |
The invention relates to an injector (3) for a de-icing device for an air intake of an aircraft turbojet nacelle, the injector (3) comprising a peripheral member (30) internally defining a passage duct (6), the peripheral member (30) com...
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WO/2024/074224A1 |
A hydraulic or pneumatic actuator (100, 200) for a valve, in particular a trip valve which may be used to cut-off the fluid supplied to an expander when a fault occurs, e.g. when pressure drops under a predetermined pressure value. The i...
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WO/2024/074256A1 |
The invention relates to a suspension system (2) for a manhole (6), in particular for a manhole (6) of a gas turbine (4), comprising: a first fastening portion (10) and a second fastening portion (11) for arrangement of connecting pieces...
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WO/2024/069086A1 |
The invention relates to a turbine engine comprising: - a first module comprising a speed reducer (3) having an input shaft (12), - a second module comprising a low-pressure compressor which is connected to the first module, - a third mo...
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WO/2024/066426A1 |
An oil and gas dual-effect seal structure for a gas turbine, comprising: a turbine rotor, a fixed sleeve, a supporting ring, a seal ring, a sleeve, an adjusting ring, a bearing, a locking gasket and a nut. The turbine rotor is sleeved wi...
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WO/2024/061740A1 |
The invention relates to a turbine engine comprising: a first splitting edge capable of separating an incoming air stream into a radially internal air stream and a secondary air stream; a second splitting edge capable of separating the r...
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WO/2024/061737A1 |
The invention relates to a turbomachine comprising: a first splitting edge capable of separating an incoming air flow into a radially internal air flow and a secondary air flow; a second splitting edge capable of separating the radially ...
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WO/2024/064620A1 |
Disclosed is a method enabling operation of a combustion system with at least two serially arranged combustion zones on fuels generally yielding varying flame speeds. First, the operating parameters of the gas turbine engine are determin...
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WO/2024/059468A1 |
Liquid fuel systems and methods are provided. A liquid fuel system includes a mixing unit and a plurality of liquid fuel supply systems. Each liquid fuel supply system is fluidly coupled to the mixing unit. The liquid fuel system further...
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WO/2024/059350A1 |
An igniter for a gas turbine engine has a shell; an insulator secured within said shell; a center electrode secured within said insulator and electrically isolated from said shell by said insulator, said center electrode having a firing ...
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WO/2024/057776A1 |
A heat-exchanging partition wall for air cooling a high-temperature component of an aircraft engine is provided with a wall that defines a cooling flow path through which cooling air flows along a first direction between the wall and a c...
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WO/2024/056975A1 |
The invention relates to a device for guiding a shaft of an aircraft turbine engine, the device comprising: - a rolling bearing (10, 11); - an annular bearing support (22); and - an oil film compression damping system (19) comprising: - ...
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WO/2024/057775A1 |
An aircraft engine combustor equipped with a cylindrical member for demarcating an internal space which extends along an axis, and a fuel nozzle which is positioned in a manner such that at least a part thereof is positioned inside the i...
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WO/2024/054295A1 |
A flow system (10) includes a flow source device (12) configured to receive fluid from a first flow line (14) and output fluid on a second flow line (16). An output (18) is in fluid communication with the flow source device on the second...
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WO/2024/054836A1 |
A dual-fuel turbine engine is a type of turbine engine that can operate using two different fuel sources, such as liquid fuel (e.g., diesel) and natural gas. For liquid fuels, the turbine engine includes a primary line to facilitate engi...
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WO/2024/054490A1 |
A turboexpander (102) comprises a rotor shaft (108) and a permanent magnetic generator and includes a process gas inlet on a downstream side of a flow control valve (126) to receive process gas into the turboexpander; the rotor shaft (10...
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WO/2024/053326A1 |
The present invention provides a cooling fluid guide for a gas turbine, the cooling fluid guide comprising: a fixed part to be fixed either to piping for supplying a cooling fluid to a cooling fluid supply hole in a turbine casing or to ...
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WO/2024/053577A1 |
This heat engine system comprises: a heat engine that is driven by gas fuel and generates exhaust gas; a waste heat recovery boiler that has a fuel heating line for generating the gas fuel by heating liquid fuel through heat exchange wit...
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WO/2024/046222A1 |
Disclosed in the present invention are a flow dividing ring and an aero engine containing same, and an aircraft. The flow dividing ring is internally provided with an annular cavity, and the flow dividing ring is connected to an air inta...
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WO/2024/048211A1 |
Provided is a gas turbine stationary blade. When a plane including a thickness direction and a blade height direction of a leading edge part at the center of an inlet of a first film cooling hole is defined as a first plane, the center o...
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WO/2024/043268A1 |
This gas turbine is provided with a combustor which can switch a fuel to be combusted between an ammonia fuel and a hydrocarbon-based fuel. The combustor has: a cylindrical body which has a cylindrical shape and through which a combustio...
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WO/2024/041680A1 |
A turbine assembly according to the present invention has passages formed in a fixing part of a second wheel of the assembly between at least some adjacent blades 1r/1s for draining the working medium that has leaked through a non-contac...
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WO/2024/042343A1 |
A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includ...
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WO/2024/034367A1 |
This suction heating system is configured to heat outside air fed to a compressor of a gas turbine. The suction heating system is provided with a suction heating unit configured to heat outside air using a heat source different from that...
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WO/2024/033588A1 |
The invention relates to an aircraft turbine engine (10) having: - a compressor (14), - an annular combustion chamber (24), - a system (32) for diffusing and straightening an air stream exiting the compressor in order to supply the combu...
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WO/2024/033585A1 |
The invention relates to a turbine engine (1) for an aircraft, comprising an annular lubrication enclosure (17) in which a speed reducer (12) is arranged, a system for lubricating the speed reducer (12) comprising a main lubrication circ...
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WO/2024/034643A1 |
This gas turbine assembly comprises: a metallic component including a bolt hole; a composite component overlapping the metallic component; a retainer including a bolt hole aligned with the bolt hole of the metallic component; and a bolt ...
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WO/2024/035537A1 |
A gas turbine engine includes an outer casing, an inner casing surrounded by the outer casing, the inner casing and the outer casing defining a casing cavity therebetween. A blower is disposed external of the outer casing and operable to...
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WO/2024/034366A1 |
This intake air heating system is configured so as to heat external air flowing in an intake air flow path communicated with a compressor of a gas turbine, the intake air heating system comprising: a first heating unit that includes a re...
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WO/2024/028551A1 |
The invention relates to an exhaust system (18) for a turbine engine, comprising a nozzle (20) at least partly delimiting a gas exhaust path. The system comprises a heat exchanger (26) comprising at least one distributor (28), at least o...
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WO/2024/028553A1 |
The invention relates to a turboprop (10) comprising: - a turbine (12) mechanically connected to an input (21) of a reducer (20); - a tail shaft (30) bearing a variable-pitch propeller (31); - a rotary electric machine (46); and - an ele...
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WO/2024/024197A1 |
A combustion system 10 comprises: a combustion chamber 13c; a cylindrical air chamber 31 which has an injection hole 31a facing the inside of the combustion chamber 13c; a fuel supply path 41 connected to the air chamber 31; and an air s...
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WO/2024/023413A1 |
Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) 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/2024/023445A1 |
Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbines (11, 2...
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WO/2024/023422A1 |
The present invention relates to a method for controlling an electrical system, comprising: processing a main command signal (IP) for commanding drawing of a mechanical power by the electrical system from an electrically hybridized turbo...
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WO/2024/023439A1 |
The invention relates to an electrical power generation and distribution system 1 for a hybrid-electric propulsion aircraft powered by at least one turbojet engine (10). The system comprises at least N ≧ 2 (N integer) distribution netw...
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WO/2024/023448A1 |
The invention relates to a propulsion assembly (10) for an aircraft, comprising a cowling panel (24) that is installed in a high-temperature region of the propulsion assembly (10) and provides a flameproof barrier, the panel (24) compris...
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WO/2024/024139A1 |
A disc for a rotating machine according to the present disclosure comprises an inner diameter side member shaped like a ring around an axis and forming a radially inner portion with respect to the axis, the inner diameter side member bei...
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WO/2024/022304A1 |
An inlet cone. The inlet cone comprises a body (2) and a nose cone portion (1), wherein the body (2) comprises an outer wall (21), and the nose cone portion (1) is connected to an end of the outer wall (21); an outer surface of the nose ...
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WO/2024/025546A1 |
A combined cycle power plant includes a gas turbine engine, which includes a compressor and a turbine. The turbine discharges a first exhaust gas stream therefrom. A heat recovery steam generator receives the first exhaust gas stream, ex...
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WO/2024/023881A1 |
Provided is a fuel supply system that can identify an internal leak model of a gear pump with high accuracy. The system comprises: a gear pump; a measurement section including an orifice and a check valve that are connected in parallel...
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WO/2024/018988A1 |
This aircraft hybrid motive power source system is installed in an aircraft and comprises: a gas turbine engine (20) that includes a low-pressure shaft (27) and a high-pressure shaft (28) as rotating shafts; a first electric generator (3...
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WO/2024/018137A1 |
The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11...
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WO/2024/018750A1 |
A gas turbine stationary blade according to the present invention comprises: a path that passes through the inside of a blade shape part so as to connect an outer cavity, which is formed on the outer side of an outer shroud in the blade ...
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WO/2024/013462A1 |
The present invention relates to a method and system for managing the drawing of mechanical power from a two-spool or three-spool turbine engine (1) for an aircraft, in which at least two electric machines (3, 4) are suitable for recover...
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