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WO/2022/064160A1 |
The invention relates to an aircraft turbine engine (10) with main axis A, comprising: an arm (18) that is radial with respect to the main axis A, extending through an air flow duct (14); a support wall (22) belonging to the radial arm (...
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WO/2022/064674A1 |
This steam turbine comprises a rotor shaft, a plurality of moving blade rows, a casing, and fixed blade rows disposed on a first side in the axial direction, relative to each of the plurality of moving blade rows. The last fixed blade ro...
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WO/2022/058672A1 |
Aircraft turbine engine (10) comprising: - a gas generator (12), - a fan (14), and - an electrical machine (70), the stator (70b) of the electrical machine (70) being connected to a power electronic circuit (78) by at least one electrica...
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WO/2022/058681A1 |
Production of a structure for a turbomachine by additive manufacturing, comprising the following steps: a) providing an element having at least one localised rough region (16), in particular produced by machining, b) using powder bed fus...
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WO/2022/055865A1 |
The invention refers to an integral or monolithic nozzle segment (30) having airfoils (33) According to an aspect of the invention a steam turbine has a casing (17) supporting multiple nozzle segments (30) forming a diaphragm (22) with t...
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WO/2022/051760A1 |
A guide vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil extending between the inner platform and the outer platform. The vane airfoil has a bow shape. A first outer seal slot and a second ou...
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WO/2022/051759A1 |
A guide vane in a gas turbine engine includes an inner platform, an outer platform, and two vane airfoils extending between the inner platform and the outer platform and spaced apart from each other. The outer platform includes a front h...
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WO/2022/049338A1 |
The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: - a casing (4) comprising an annular hook (38), - a movably mounted impeller (16), - a ring (30) extending opposite the impeller in a direction ...
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WO/2022/051100A1 |
An alignment tool includes a mounting flange, a support leg fixedly coupled to the mounting flange and cooperating with the mounting flange to define a partial annular ring that extends in an arc between 190 degrees and 350 degrees, and ...
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WO/2022/049716A1 |
A Co-based alloy product according to the present invention is characterized by having a chemical composition containing, in % by mass, 0.08 to 0.25% of C and 0.003 to 0.2% of N in which the total of C and N is 0.083 to 0.28%, also conta...
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WO/2022/051758A1 |
A guide vane (200, 300, 400, 500, 700) in a gas turbine engine (100) includes an inner platform (202), an outer platform (204), and an airfoil (206) extending therebetween. Side surfaces (302, 304) of the inner platform and outer platfor...
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WO/2022/049717A1 |
A Co-based alloy product according to the present invention is characterized by having a chemical composition containing, in % by mass, 0.08 to 0.25% of C and 0.003 to 0.2% of N in which the total of C and N is 0.083 to 0.28%, also conta...
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WO/2022/039122A1 |
Turbine equipment (100) comprises a low-pressure turbine (30) and a plurality of shields that cover the low-pressure turbine (30), and each of the plurality of shields has a layered structure with respect to the other shields. Preferably...
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WO/2022/034783A1 |
This stator blade segment comprises a circumferentially extending outer blade ring, a stator blade extending radially inward from the outer blade ring, and a sealing member. The stator blade has a cavity that is formed in the interior of...
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WO/2022/035460A1 |
A gas turbine engine includes a compressor section, a combustor section, a turbine section, a hot gas path and a layered component (600) including a substrate (502) and a thermal barrier coating (TBC) (602) having: a single layer of 6-15...
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WO/2022/034756A1 |
This stationary turbine blade comprises: a stationary blade main body extending in the radial direction intersecting the flow direction of steam; a hydrophilic region which is formed on the surface of the stationary blade main body and w...
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WO/2022/018197A1 |
A method (190) for manufacturing a vaned component (100) of a turbomachine is provided. The method includes providing a base portion ( 115), additively manufacturing, on top of the base portion (115), a plurality of vanes (150) and a plu...
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WO/2022/003276A1 |
The present invention relates to a method for manufacturing a turbine nozzle guide vane from a ceramic matrix composite material.
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WO/2021/259571A1 |
It is described a nozzle casing (1) for a steam turbine (1000), comprising a first section (2) extending at least partly along a circumferential direction of the steam turbine (1000), wherein the first section (2) defines a first chamber...
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WO/2021/259862A1 |
The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detac...
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WO/2021/255383A1 |
Aircraft turbomachine (10), comprising: a centrifugal compressor (14), a combustion chamber (24), the combustion chamber being supplied by the compressor via a diffuser (34) and via a straightener (36), and a heat exchanger (38), the exc...
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WO/2021/255384A1 |
Aircraft turbomachine (11), comprising: - a centrifugal compressor (12), - an annular combustion chamber (24), - an annular casing (29) extending around the chamber and delimiting an annular space (E) in which the chamber is situated, an...
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WO/2021/250339A1 |
A turbomachine of longitudinal axis (X-X') comprising a fan that delivers a main airflow (F) and a separating member (20) that is configured to separate said airflow (F) into a primary airflow (F1) flowing in an inner duct (VI) and a sec...
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WO/2021/245339A1 |
The invention relates to a turbine nozzle for a turbine engine, comprising two annular walls (36, 38) extending about the same axis (X), the walls (36, 38) being connected to each other by blades (34) having an aerodynamic profile, the n...
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WO/2021/246247A1 |
A method of reprocessing a metal product according to the present invention including: a welding process for welding a dummy member to the metal product; a reprocessing process for reprocessing the metal product in a state in which the m...
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WO/2021/235081A1 |
This stator vane has: a vane body that extends in a radial direction; and a shroud provided to an end on a first side in the radial direction of the vane body. The shroud has a first circumferential direction end surface facing a first s...
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WO/2021/235314A1 |
This drain removal monitoring device for monitoring drain removal in a steam turbine, performed by a fluid outside at least one hollow stator vane, which includes an internal space, being sucked into the internal space through a slit for...
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WO/2021/227443A1 |
A connecting member and an anti-thermal mismatch connecting device. A rod portion (24) of a connecting member (2) comprises a material-reducing hollow segment (21) and a cylindrical segment (22), the material-reducing hollow segment (21)...
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WO/2021/224565A1 |
Turbomachine turbine guide vane extending about a central axis (X), comprising at least one radially external shroud (43), at least one radially internal shroud (42), and at least one blade (50) made of a ceramic matrix composite, distin...
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WO/2021/219960A1 |
The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material ...
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WO/2021/219949A1 |
The invention relates to an annular intermediate casing (22) for a turbomachine through which an aerodynamic airstream circulates, comprising: - a radially internal shroud (31), - a radially external shroud (32), - at least one stator bl...
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WO/2021/209707A1 |
The invention relates to a turbine (1) for a turbine engine extending along an axis, comprising an annular casing (4) and at least one turbine stage (1) comprising a nozzle (2) and a rotor impeller wheel (5) surrounded by a sealing ring ...
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WO/2021/199718A1 |
A secondary flow suppression structure (10) comprising: a turbine rotor blade (12) that has an outer shroud (14); a turbine stator blade (22) that has an outer band (24) and that is positioned behind the turbine rotor blade (12); a seal ...
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WO/2021/199802A1 |
A static blade (30) provided in the rear of a rotor blade (21) comprises a blade main body (32) having a blade-shaped cross-section (31). The maximum blade thickness position (M) of the blade main body (32) in the blade-shaped cross-sect...
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WO/2021/200918A1 |
A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and whi...
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WO/2021/198624A1 |
The invention relates to an intermediate casing (1) for a turbomachine, comprising: o an inner wall (3) having an outer radial surface (30), o an outer wall (4) having an inner radial surface (40), and o a first arm (21), a second arm (2...
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WO/2021/200954A1 |
This steam turbine comprises: a rotating shaft that extends along an axis; a plurality of rotor blades that are arranged in the circumferential direction and that extend in a radial direction from the outer circumferential surface of the...
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WO/2021/193628A1 |
A turbine blade comprising an airfoil part including a front edge, a rear edge, and a pressure surface and a negative pressure surface extending therebetween. A cooling path is formed inside the airfoil part. The cooling path includes: a...
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WO/2021/191529A1 |
The invention relates to a dynamic sealing device (220) for a measuring system (200) comprising a measuring probe (210) intended to pass through a first motor compartment (140) of a turbomachine and to measure a physical variable in a se...
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WO/2021/191543A1 |
Turbine stator blade made of a ceramic matrix composite material comprising at least one hollow blade profile (100, 200, 300, 400, 500) having a trailing edge (BF) and a leading edge (BA), the blade comprising a first portion (110, 210, ...
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WO/2021/193610A1 |
This turbine blade is provided with: a blade shape part which includes front and rear edges, and a pressure surface and a suction surface extending between these edges; and a cooling passage formed inside the blade shape part. The coolin...
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WO/2021/191540A1 |
A distributor made up of sectors (15) of stator vanes (5) connected, on the outside, to a stator comprises an inner platform divided into an outer portion formed of sectors and joined by radial slide connections to a continuous inner rin...
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WO/2021/188114A1 |
A turbine operable to produce a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of th...
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WO/2021/186135A1 |
Disclosed is a turbomachine rotary assembly comprising a rotor having at least two consecutive rotor stages (20a, 20b) provided with a plurality of movable blades and, an annular rotor ferrule (30) connecting the two consecutive rotor st...
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WO/2021/186796A1 |
This stator vane is at least provided with a blade body disposed in a combustion gas flow channel through which a combustion gas flows, a shroud that defines a part of the combustion gas flow channel, and an impingement plate attached to...
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WO/2021/181038A1 |
Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the ...
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WO/2021/170944A1 |
Assembly in a turbine comprising: - at least one turbine ring made of a ceramic composite having a silicon carbide SiC matrix and fibers, the ring comprising a plurality of sectors (10) arranged circumferentially end to end, each of the ...
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WO/2021/170952A1 |
One aspect of the invention relates to a nozzle blade (100) for a turbine engine comprising a blade body (110) in which at least one through-cavity (122) is provided extending between an inner end (111) of the blade and an outer end (112...
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WO/2021/173129A1 |
A gas turbine engine includes a rotor rotatable about a central axis. The gas turbine engine includes a turbine stage including a stationary portion and a rotating portion made up of a number of rotating blades and a plurality of station...
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WO/2021/170167A1 |
The present invention relates to a guide blade arrangement (20) for a turbomachine (1), having a guide blade aerofoil (22), and having a platform (21), wherein the guide blade aerofoil (22) is arranged on a side (21.1), which faces a gas...
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