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WO/2024/079461A1 |
There is disclosed a rocket engine arranged to deliver one or more propellants to a combustion chamber of the rocket engine for generating motive thrust. The rocket engine comprises an electrical transmission system, a turbine generator ...
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WO/2024/078322A1 |
A special device for measuring the center of a connecting shaft of a steam turbine, said device comprising: a main body assembly (100), comprising a gauge frame (101), a support (102), a fastener (103) on the gauge frame (101), an intern...
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WO/2024/077655A1 |
The present invention relates to the technical field of steam turbine systems for feed water pumps, and in particular to a variable-frequency generation and heat regeneration integrated steam turbine system for a feed water pump. The sys...
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WO/2024/080158A1 |
Provided is a cryogenic power generation apparatus which is provided with a thrust bearing device placed on one side in the axial direction of a rotor shaft as compared to a first journal bearing device in the inner circumferential side ...
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WO/2024/081542A1 |
A handling system includes an elongated member including a first end and a second end, and a first bend therein. The elongated member is positioned in a slot of the turbine shroud. A base retention member extends from the first end of th...
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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/2024/076859A1 |
A vibration damping system includes a vibration damping element for a turbomachine nozzle or blade. A body opening extends through the turbomachine nozzle or blade between the tip end and the base end thereof. A vibration damping element...
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WO/2024/075468A1 |
In this method for modifying a steam turbine, a blade removal step and a flow path partition step are implemented. In the blade removal step, a plurality of moving blade rows including a moving blade row on the most axially downstream si...
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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/2024/069083A1 |
One aspect of the invention relates to a nozzle (1) comprising: - a spray gas supply pipe (2); - a mixing chamber (3) for mixing spray gas and powdered material into an accelerated mixture which is connected, via an upstream end (31), to...
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WO/2024/073580A1 |
A method of repairing a turbine blade includes positioning the turbine blade within a system including a machining tool; determining a first distance between a surface of a first PSP attached to a tip shroud of the turbine blade and a da...
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WO/2024/070490A1 |
Provided is a geothermal power generation system with which it is possible to control silica scale deposition. This geothermal power generation system comprises: a production well; a steam-water separator which separates a geothermal f...
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WO/2024/068224A1 |
The invention relates to a turbomachine (1), in particular for a fuel cell system (100) of a vehicle (200), for example of a utility vehicle, the turbomachine comprising a rotor shaft (19), an expander wheel (15) that is fastened on the ...
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WO/2024/066255A1 |
A high-pressure turbine active clearance control device, comprising a high-pressure turbine casing (1), gas collection casings (2), an impingement heat exchange tube (3) and a fluid oscillator (4). The gas collection casings (2) are disc...
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WO/2024/062189A1 |
The invention relates to a sealing device (1) comprising: a ring (10) that comprises a main sealing lip (12) and a secondary sealing lip (14), the main sealing lip having an inner surface (11), the secondary sealing lip (14) having a rad...
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WO/2024/059469A1 |
A guide for cutting a dowel pin of a rotor assembly is provided. The guide includes a catch basin, including a first catch basin portion and a second catch basin portion, and a shim. The first catch basin portion and the second catch bas...
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WO/2024/056958A1 |
The invention relates to a method for producing an abradable ceramic composite coating on a substrate, the method comprising: obtaining (E1) a composition (30) in powder form comprising a matrix powder and a ceramic filler hydrated precu...
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WO/2024/056133A1 |
The invention relates to an inflow device (7) of a spiral channel (6) of an exhaust gas guide section (2) of an exhaust gas turbocharger (1), said inflow device comprising an inflow section (8) and a flow section, the inflow section (8) ...
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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/2024/056134A1 |
The invention relates to an exhaust gas guide section (2) of an exhaust gas turbocharger (1), said exhaust gas guide section comprising a spiral channel (6) which is designed to surround at least part of a turbine wheel (3) of a rotor (4...
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WO/2024/053148A1 |
This turbine T includes an impeller 2 and a housing 5 that houses the impeller 2. The housing 5 includes an inlet that is in fluid communication with an exhaust port of an engine, a first space S1 that houses the impeller 2, a second spa...
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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/2024/048830A1 |
The present invention relates to a high-efficiency axial flow turbine (100) having improved functions. To this end, the present invention comprises: a housing (110) which allows fluid to be introduced into the axial flow turbine through ...
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WO/2024/045240A1 |
A supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃, belonging to the technical field of turbines. The present invention aims to solve the problem that sealing of supercritical carbon dioxide ...
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WO/2024/038492A1 |
This supercharger seal structure comprises at least a plurality of seal members provided to a seal gap formed between a rotating member, which includes a rotating shaft and a rotating wheel, and a stationary member, which includes a hous...
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WO/2024/038250A1 |
A rake assembly (100) for measuring fluid flow parameters in a fluid flow rig (10), the rake assembly (100) comprising : a rake assembly support frame (500); a housing (102) mounted on the rake assembly support frame (500); the housing (...
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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/2024/028553A1 |
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/2024/024791A1 |
This rotary device (100) comprises: an impeller 1; a plurality of movable-type vanes 2 which are disposed upstream or downstream from the impeller 1 and operated so as to adjust the cross-sectional area of a flow passage; and an inner wa...
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WO/2024/021252A1 |
An air guide casing inner cylinder of a gas turbine having double combustion chambers, comprising an inner cylinder body (2, 3), a lower flow guide plate (4), and an upper flow guide plate (5). The two circumferential sides of the lower ...
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WO/2024/023408A1 |
According to one aspect, the invention relates to a device for de-icing a turbine engine blade (1) of axis Y, comprising a blade (2) that is rotatably movable about a pivot (20) of radial axis X and comprising an electrical resistor (60)...
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WO/2024/020155A1 |
A turbocharger housing includes a first fluid passage and a second fluid passage. The first fluid passage includes an exhaust gas inlet, a volute, and an exhaust gas outlet. The volute extends from the exhaust gas inlet in a circumferent...
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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/2024/018218A1 |
There is disclosed a turbine housing (2) for a turbocharger. The turbine housing comprises a flange (4) and a volute 6. The flange (4) has an engagement surface (14) and a first inlet opening (12) in the engagement surface (14). The volu...
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WO/2024/009430A1 |
Provided is a variable nozzle unit including: a first plate-like member including a ring-shaped first plate part; a second plate-like member including a ring-shaped second plate part that forms a gas flow path between the second plate pa...
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WO/2024/007460A1 |
The present invention relates to the technical field of aeroengines, and disclosed is an air-bleed mechanism for a turbine engine, which solves the problem that existing air-bleed mechanisms for turbine engines can hardly meet the requir...
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WO/2024/003475A1 |
The present invention relates to an oil tank (40) for an aircraft turbine engine, comprising: an enclosure (54) capable of containing the oil and having a main axis intended to be oriented vertically in the mounting position; an oil inle...
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WO/2024/003641A1 |
A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blades may include a dual pin-root design to secure the blade fan to a hub and a shroud...
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WO/2024/003507A1 |
Disclosed is a turbomachine (10) having an oil-recovery device comprising, between mutually rotatable first and second members (14, 16), a tubular tab (54) of the first member (14) surrounded by a tubular extension (56) of a shroud (42) ...
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WO/2023/247847A1 |
The present invention relates to an oil tank (40) for an aircraft turbomachine, the oil tank comprising: a main chamber (54) suitable for containing oil; an inlet (66) for oil mixed with air; and an oil outlet (72), the invention being c...
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WO/2023/247846A1 |
The invention relates to an oil tank (40) for a turbomachine, the oil tank comprising an oil chamber having a main axis and walls defining a first compartment (56) and a second compartment (58) which is separated from the first compartme...
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WO/2023/248728A1 |
This method comprises: a shaping step in which, while a metal powder is being disposed on a base plate, the metal powder is bonded together and solidified to thereby form an additively manufactured object having inner passages and discha...
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WO/2023/249815A1 |
A thermal power plant comprising: at least ah expander system, an energy-supply fluid, an energy-receiving fluid, and a direct-contact heat and mass exchanger, said exchanger facilitating heat and mass transfer from said energy-supply fl...
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WO/2023/242496A1 |
The invention relates to an assembly for a turbine engine of longitudinal axis (X), comprising: an exhaust cone (40) having an annular wall (44); an exhaust casing arranged upstream of the exhaust cone (40); a connection flange (46) disp...
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WO/2023/237617A1 |
A flange assembly (110) for a turbocharging system (100) is described. The flange assembly comprises a housing component (112) of the turbocharger system (100) having a first flange portion; and an auxiliary component (111) of the turboc...
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WO/2023/237154A1 |
The invention relates to an exhaust gas treatment apparatus (1) for an aircraft engine (2), the exhaust gas treatment apparatus comprising an exhaust gas channel (7), through which an exhaust gas of the aircraft engine (2) can flow, a fi...
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WO/2023/231218A1 |
A turbine guide vane mounting structure, comprising a metal cover plate and CMC turbine guide vanes. The metal cover plate comprises at least one protrusion and at least one inclined surface, and exhaust slots are further formed in the i...
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