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WO/2023/282078A1 |
A turbine stator vane comprising: a vane body; a shroud formed at an end of the vane body in a vane height direction; a fillet portion joining the vane body and the shroud; and a plurality of cooling holes in a bottom plate contacting a ...
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WO/2023/273768A1 |
The present invention relates to the technical field of turbomachines. Disclosed is a turbomachine, comprising a seat body and a reducer. An outer impeller is rotatably arranged in the seat body. The outer impeller comprises an outer whe...
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WO/2023/276385A1 |
A turbine stator vane comprising: a stator vane body extending in a radial direction intersecting the flow direction of steam; a recovery potion that is formed on the surface of the stator vane body, and recovers a liquid film flowing al...
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WO/2022/270387A1 |
This first-stage stationary blade segment comprises an outer ring extending in a circumferential direction, and a plurality of first-stage stationary blades attached on the radially inner side of the outer ring so as to be aligned in the...
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WO/2022/263752A1 |
The invention relates to an unducted rectifier for a turbomachine comprising: - stator vanes (23) each comprising a root (25) and a blade (24) radially projecting from the root, the root comprising two half-platforms (40A, 40B) extending...
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WO/2022/255229A1 |
Provided is a technology for employing a simulation to precisely evaluate creep deformation behavior of a nozzle diaphragm of a steam turbine that is operated in a power generation plan involving large output variations. A damage evalu...
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WO/2022/255051A1 |
This stationary blade segment comprises a first stationary blade, a second stationary blade, and a connecting implement that connects the first stationary blade and the second stationary blade. A first shroud of the first stationary blad...
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WO/2022/229548A1 |
The invention relates to a device (30) for shaping at least one fibrous preform of a bladed part (10) of a turbine engine, the device comprising a mould (34) formed of multiple parts nested inside one another, the mould defining an inter...
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WO/2022/229637A1 |
An electrode assembly for electrochemically machining a cavity of a component is disclosed. The electrode assembly comprises: an electrode, a mounting body, and an urging means. The electrode comprises a plurality of conductive elements,...
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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/2022/223905A1 |
The invention relates to a turbine ring assembly (2) extending around an axis (X-X), comprising a plurality of ring sectors (10) made of ceramic matrix composite material forming a turbine ring (4) and a ring support structure (6) held b...
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WO/2022/219282A2 |
Disclosed is a turbine comprising a casing and a turbine nozzle having an outer metal shroud (9) that is secured the casing, an inner metal shroud, and a plurality of nozzle sectors (20) that are made of CMC and form a ring extending bet...
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WO/2022/214323A1 |
The invention relates to a group of stator vanes (100) for a row of stator vanes of a stage of a turbomachine compressor, the vanes of the group of stator vanes (100) being close together and affording easy assembly. The group of stator ...
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WO/2022/215579A1 |
This supercharger gas casing is provided with a scroll part in which a plurality of scroll flow paths are formed at the same positions in the axial direction of a turbine. The plurality of scroll flow paths include a first scroll flow pa...
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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/2022/202636A1 |
This stator blade comprises a blade body, a first insert, a second insert, and an end cover. The blade body has a first blade air passage and a second blade air passage extending in the blade height direction within the blade body. Each ...
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WO/2022/201988A1 |
The curvature adjustment method according to the present invention is applied to an arc-shaped stator blade segment in which a plurality of stator blades are disposed side by side in the circumferential direction on the outer peripheral ...
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WO/2022/185164A1 |
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 blade fan is tensioned at the tips of the plurality of blades. By tensioning the tips o...
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WO/2022/185163A1 |
A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blad...
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WO/2022/180329A1 |
The turbomachine subassembly comprises: - at least one low-pressure nozzle ring, the nozzle ring comprising a root (38) integral with the nozzle ring; - a clamp (40) configured so as to fasten the root to a casing of the turbomachine; an...
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WO/2022/174986A1 |
The invention is about a transition (01) of a combustion section (06) of a gas turbine (04) comprising a bulge (23) and an exit frame (33) and in-between a channel wall (02), wherein a flow channel (03) crosses the transition from an ups...
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WO/2022/171676A1 |
The present document describes a gas outlet housing for an exhaust-gas turbocharger. The gas outlet housing comprises a diffuser housing portion to slow down an exhaust gas flow entering, in an inflow direction, the diffuser housing port...
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WO/2022/171955A1 |
Turbomachine guide vanes assembly (10) extending about an axis (70) and comprising blading (20) mounted between an outer shroud (42) and an inner shroud (30), and a position-maintaining device (60) configured to be arranged in an elastic...
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WO/2022/171669A1 |
The invention relates to a gas outlet housing for a turbocharger. The gas outlet housing comprises a diffuser housing portion for decelerating a first exhaust gas flow flowing out of a turbine of the turbocharger in an inflow direction i...
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WO/2022/168262A1 |
A blade member having a groove structure formed on a surface, wherein the groove structure comprises a plurality of first groove structures, a plurality of second groove structures, and a third groove structure. The plurality of first gr...
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WO/2022/168951A1 |
This stationary vane ring comprises a vane group having a plurality of vanes arrayed in the circumferential direction of an axis, a shroud segment in which the radial ends of the plurality of vanes of the vane group are connected to form...
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WO/2022/162299A1 |
The invention relates to a stator ring (10) for an aircraft turbine engine, said stator ring (10) comprising two coaxial annular shrouds (20, 30), an inner shroud (20) and an outer shroud (30) respectively, which are connected to each ot...
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WO/2022/163030A1 |
A turbine stator vane (24) comprising a vane body (40) and a shroud (60) formed at an end part of the vane body in a vane height direction, wherein the shroud comprises: a bottom plate (82) in contact with a combustion gas flow path; a c...
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WO/2022/157097A1 |
The invention relates to a sandblasting mask (50) and to the use thereof for sandblasting blade tips in a method comprising: a step of positioning a plurality of sandblasting masks (50), each blade passing through an opening (58) in a ma...
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WO/2022/148928A1 |
Stator assembly for straightening an air flow, turbojet engine, turbofan engine and aircraft, the assembly comprising a plurality of stator vanes distributed around an axis of revolution of the stator assembly, wherein for each stator va...
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WO/2022/150036A1 |
A turbine vane (200) in a gas turbine engine includes an inner platform (202), an outer platform (204), and a vane airfoil (206) positioned therebetween. The vane airfoil includes a first cooling passage (212) extending between the outer...
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WO/2022/148993A1 |
The invention relates to a turbine housing (100) for use in a turbocharger, comprising a wheel housing space (120), an inlet (130), at least one volute (140), and a tongue (150) that projects from a separation wall (160). The tongue (150...
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WO/2022/129749A1 |
Guide vane assembly (100) for a turbomachine, comprising: an inner platform (102) and an outer platform (101); a plurality of vanes (110) positioned between the inner and outer platforms, the vanes being made of a composite material comp...
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WO/2022/123140A1 |
The invention relates to a guide vane assembly (300) of an aircraft turbine engine, the guide vane assembly being segmented into a plurality of segments (301) arranged circumferentially next to one another about an axis. The guide vane a...
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WO/2022/117413A1 |
The invention relates to a turbocharger (1) with an integrated catalytic converter substrate block (3) and to a hybrid vehicle (50) which has such a turbocharger. The turbocharger (1) has a turbine housing (21), a turbine wheel (12), and...
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WO/2022/118500A1 |
Provided is a blade capable of optimizing outflow angle in substantially the entirety of the hub region and the tip region, particularly in the blade-end-side hub region and the blade-end-side tip region. The blade is composed of a bas...
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WO/2022/112685A1 |
The invention relates to a turbine engine case (1), extending around an axis, said case (1) comprising: a hub comprising an outer wall (21) and an inner wall (22) between which an annular flange (23) extends; an outer shell (3); a plural...
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WO/2022/113570A1 |
This turbine includes: a rotor having a rotor body which can rotate around an axial line, and a plurality of rotor blades arranged in the circumferential direction along the outer peripheral surface of the rotor body; a casing covering t...
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WO/2022/107467A1 |
Provided is a steam turbine member that suppresses adhesion of scales over a long period of time without impairing the corrosion resistance or the like of a turbine. The present invention provides: a steam turbine member including a ha...
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WO/2022/103585A1 |
A compact heat exchanger (170) is disclosed for re-circulating bleed air from a combustor into an inlet (110) and/or exhaust (150) of a gas turbine engine (100). In an embodiment, the heat exchanger (170) may comprise a plurality of airf...
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WO/2022/101029A1 |
The invention relates to a guide vane wheel (4) of a turbomachine, having a plurality of guide vanes (41), which form a vane row (42) and are designed to extend radially inwards in a flow path (6) of the turbomachine, and two boroscope a...
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WO/2022/101166A1 |
A guiding array (200; 600) for a flow duct system (100; 200; 300; 500) includes a series of internested annular guide vanes (202), leading edges (230) or other common parts of the guide vanes being arranged to be positioned different dis...
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WO/2022/096170A1 |
The invention relates to a method for providing manufacturing instructions for the additive manufacturing of a component (10), wherein design vectors (Vr, Vc) for a layer (L) that is to be additively manufactured for the component (10), ...
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WO/2022/090643A1 |
A fairing element (33) is intended to be placed in a fluid flow passage (F), to surround an obstacle (31) which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairi...
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WO/2022/090667A1 |
An assembly for a turbine comprises a plurality of sectors (40) which are adjacent to one another, each actor comprising at least one connecting edge (42, 43) of composite material with a ceramic matrix, each connecting edge comprising a...
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WO/2022/087279A1 |
An exhaust gas aftertreatment system includes a housing assembly, a first catalyst member, and a second catalyst member. The housing assembly includes an upstream housing, a decomposition housing, a distributing housing, and a catalyst m...
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WO/2022/084611A1 |
The invention relates to a turbofan engine (1) comprising a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes (10) extending in the secondary duct, downstream of a fan (2), at least one servo extending ...
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WO/2022/069845A1 |
The invention relates to a turbine blade (60) for a turbine engine, comprising an aerofoil (61) and a platform (62). The platform (62) comprises an internal channel (80) having a suction opening (81) which opens on a first surface (71) o...
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WO/2022/069835A1 |
The invention relates to a turbomachine module having a longitudinal axis X, comprising a shroudless propeller (2) which is rotated about the longitudinal axis X by a drive shaft (9, 10), which is connected at least to a compressor rotor...
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WO/2022/064670A1 |
This steam turbine is provided with a rotor shaft which rotates about an axis, a plurality of rows of moving blades which are fixed to the outside, in the radial direction, of the rotor shaft, and which are disposed spaced apart in the a...
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