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WO/2024/081583A1 |
A system is provided with a controller configured to receive a computer model of a mold configured to cast a part. The computer model has a variable wall thickness of the mold thermally tailored to a geometry of the part. The controller ...
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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/2024/073340A1 |
A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in one of TABLE I or TABLE II. The Cartesian coordin...
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WO/2024/073341A1 |
A stator vane is provided. The stator vane including an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in Table I. The Cartesian coordina...
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WO/2024/062807A1 |
A turbine stator vane according to at least one embodiment of the present disclosure comprises a first partition wall and a second partition wall which partition the internal space of an airfoil, and a plurality of through-holes penetrat...
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WO/2024/062179A1 |
The invention relates to an inter-turbine casing (8) for a turbine engine of the turbine vane frame type, which casing acts as a turbine distributor in such a turbine engine, the inter-turbine casing comprising an inner shroud (9), an ou...
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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/2024/056961A1 |
Sector (6) of a guide vanes assembly for a turbine of an aircraft turbomachine, the sector (6) comprising an outer platform (7) and an inner platform (8) which are coaxial along an axis (X), the sector (6) further comprising at least one...
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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/2024/052631A1 |
The invention relates to a guide vane (33B) for attachment to a stator shroud of a gas turbine engine, comprising: - a profiled part (36B) intended to extend in a gas flow in order to guide the gas flow, the profiled part (36B) having a ...
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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/2024/048830A1 |
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/2024/048211A1 |
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/2024/044514A1 |
An assembly can include an exhaust gas turbine housing including inner and outer walls that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at t...
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WO/2024/041970A1 |
A turbine vane (TV) for a gas turbine, comprising: - an airfoil (AF) having a suction side wall (SSW) and a pressure side (PSW) wall encompassing at least one central cavity (CC), both walls (SSW, PSW) extending, when the turbine vane (T...
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WO/2024/040667A1 |
A 15MW supercritical CO2 axial flow back-pressure type turbine having volute casing air inlet, comprising a front bearing box (1), an air cylinder (2), a pressure-balancing pipe (3), a sealing member (4), a rear bearing box (5) and a rot...
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WO/2024/037803A1 |
The invention relates to a turbine (10) for an exhaust gas turbocharger, with a turbine housing (12), which has flutes (14, 16) through which exhaust gas can flow, with a turbine wheel, with a bypass channel (24), via which the turbine w...
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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/2024/035537A1 |
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/2024/018049A1 |
The invention relates to an assembly (4; 40) for a turbine engine (1) comprising a wall (6) having a guide surface (8) for guiding an air flow (F1) and a row of stator vanes (10; 100) extending from the wall and arranged annularly about ...
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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/2024/018218A1 |
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/2024/017261A1 |
Disclosed in the present invention are a turbine guide vane and a turbine containing same, and an aeroengine. The turbine guide vane comprises a guide vane body made of CMC material. The turbine guide vane further comprises a cover plate...
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WO/2024/004529A1 |
This gas turbine stator blade is provided with: a leading edge part partition that divides a cavity inside the blade into a leading edge side cavity and a trailing edge side cavity; a negative pressure surface side partition wall that is...
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WO/2024/004509A1 |
This stator blade has an airfoil, a plurality of blade air passages, and a plurality of rear end air passages. The plurality of blade air passages are arranged side by side from the side of the leading edge of the airfoil to the side of ...
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WO/2023/246804A1 |
A turbine guide vane structure, comprising a CMC component and a metal cover plate, the CMC component comprising an edge plate, and the edge plate being used for acting in concert with the metal cover plate; an axial force applying membe...
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WO/2023/249757A1 |
A pneumatically variable nozzle vane (200) is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more ...
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WO/2023/241450A1 |
Provided is a turbine guide vane structure. The structure comprises a CMC component and a metal cover plate. The CMC component comprises a blade body and an edge plate, the edge plate being matched with the metal cover plate. At least pa...
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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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WO/2023/234134A1 |
This stator blade comprises a blade body having a cross-sectional shape that forms a blade profile. The blade body includes: a trailing end space and an adjacent space that are located between a leading edge and a trailing edge; and a pl...
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WO/2023/232028A1 |
A turbine guide vane mounting structure, comprising an upper cover plate, a lower supporting plate and a turbine guide vane located between the upper cover plate and the lower supporting plate. The turbine guide vane comprises an upper e...
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WO/2023/233096A1 |
The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interio...
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WO/2023/234946A1 |
A stator vane assembly defining a chordwise direction and a crosswise direction perpendicular to the chordwise direction is provided. The stator vane assembly includes: an attachment plate; and an attachment assembly coupled to the attac...
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WO/2023/227126A1 |
A turbine outer ring connection structure comprises a turbine outer ring, a middle-layer casing and a plurality of connection assemblies, wherein each connecting assembly comprises an elastic beam and a connection piece, the bottom of th...
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WO/2023/218723A1 |
This variable stator blade is provided with a stator blade body extending in a blade height direction, and a blade rotational shaft rotatable so as to change the angle of the stator blade body with respect to a flow direction of a workin...
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WO/2023/214507A1 |
A plurality of circumferentially-arranged split plates retained by a seal-ring retention ring include a plurality of first split-plate groups that are circumferentially arranged on one circumferential side of the seal-ring retention ring...
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WO/2023/198980A1 |
The invention relates to a stator part (20) comprising a platform (22), a first blade (24), a second blade (26), and a fin (28) having a leading edge (30) and a trailing edge (32), the fin extending opposite an upper surface (124) of the...
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WO/2023/198981A1 |
The invention relates to a stator part (20) of a turbine engine, comprising a platform (22), a blade (24, 26) extending radially relative to a central axis (A), and a fin (28) extending radially from a fin root (44) to a fin tip (46), th...
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WO/2023/198979A1 |
The invention relates to a turbine engine motor having an unducted fan, the motor comprising a plurality of guide vanes (10) made of composite materials. Each of the guide vanes is intended to be fixed only to an inner fixed structure (2...
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WO/2023/187297A1 |
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner e...
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WO/2023/187296A1 |
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner e...
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WO/2023/183106A1 |
The disclosed technology includes an axial fan assembly for an air handling unit. The axial fan assembly can include an axial fan that is configured to direct a flow of air along an airflow path through the axial fan assembly and a stato...
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WO/2023/180071A1 |
The invention relates to a nozzle ring (10) for a radial turbine. The nozzle ring (10) comprises a first ring element (11), a second ring element (12), and a plurality of guide vanes (13) arranged between the first ring element (11) and ...
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WO/2023/180668A1 |
The invention relates to a turbine engine module, in particular an aircraft turbine engine (10), comprising: - an annular casing (52) having an internal wall (53) forming a channel wall; and - a nozzle (32) surrounded by the casing and c...
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WO/2023/175339A1 |
There is disclosed a turbine dosing system for a turbocharger. The turbine dosing system comprises a turbine inlet passage (112), a turbine wheel chamber and a turbine outlet passage (116). The turbine inlet passage is configured to rece...
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WO/2023/175338A1 |
There is provided a turbine for a turbocharger, the turbine comprising: a turbine inlet passage (510) configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a ...
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WO/2023/171752A1 |
Provided is a method for cooling a turbine stationary blade. A turbine comprises: an airfoil; and an outer shroud and an inner shroud that are provided on a radial outer edge of the airfoil. The airfoil comprises a plurality of air chann...
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