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WO/2022/054777A1 |
In a gas turbine clearance control system according to the present invention, a control device operates a regulating device such that a first flow rate becomes greater than a second flow rate if in a stable load state in which the fluctu...
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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/2022/051758A1 |
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/2022/049339A1 |
A turbomachine part (10) of an annular assembly comprises a structural body (11) and a connecting edge (12) integral with the structural body. Each connecting edge comprises at least one groove (120, 121) intended to receive a sealing ta...
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WO/2022/045446A1 |
The present invention provides a steam turbine comprising: a steam injection port; a steam distribution container, connected to the steam injection port, that provides a single chamber formed in an elongated shape along the front of the ...
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WO/2022/046341A1 |
An abradable powder composition is includes a metal component, a lubricant component, and a polymer component. A portion of the metal component is wrapped in the lubricant component to achieve high lubricity and abradability. The abradab...
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WO/2022/040553A1 |
Technologies are described herein for a seal assembly for an engine, the seal having a circular carbon graphite mating surface and a circular carrier mating surface. A planar face of the circular carrier mating surface includes a circula...
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WO/2022/019878A1 |
An intershaft seal assembly (20) for use between a rotatable outer structure (21) and an inner structure (22) within a turbine engine is presented. The assembly (20) includes a primary sealing ring (23), a translatable carrier (24), a se...
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WO/2022/018385A1 |
The invention relates to a turbine (7) comprising a first rotor (25) and a second rotor (27) capable of pivoting about a longitudinal axis (X) in two opposite directions of rotation, the first rotor (25) comprising a radially outer drum ...
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WO/2022/014336A1 |
A turbine for cryogenic power generation that is provided to a heat transfer medium circulation line configured so as to circulate a heat transfer medium for heating liquefied gas, said turbine comprising: a rotor shaft; a casing that ho...
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WO/2022/008049A1 |
A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by th...
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WO/2022/002832A2 |
The invention relates in particular to a three-dimensional screen printing method for producing a green part (20) from printing material (11) for a powder metallurgical component (30), wherein the printing material (11) contains powder, ...
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WO/2022/002406A1 |
Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at l...
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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/2021/246999A1 |
A ring segment arrangement of a gas turbine (10), the gas turbine having a rotational axis and a gas path for channelling a main working gas flow (34a). The ring segment arrangement forming part of the gas path and comprising a first rin...
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WO/2021/225631A1 |
A highly adaptive seal for use in advanced aircraft propulsion and missile systems is provided. The seal is capable of effectively limiting invasive thermal energy and corrosive airflow from entering the internal systems and hardware of ...
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WO/2021/224561A2 |
Platform (4) for an aircraft turbomachine fan rotor, said platform (4) being configured to be secured to a fan disc between two adjacent fan blades, and the platform (4) further comprising a longitudinal wall (5) defining an aerodynamic ...
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WO/2021/220950A1 |
A seal device according to at least one embodiment comprises three or more arcuate fins arranged in an axial direction. The arcuate fins include: a first fin, which is one of two outermost fins positioned farthest to the outer side in th...
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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/2021/216090A1 |
A gas turbine engine includes a stationary component, a rotating component rotatable relative to the stationary component, and a non-contact seal assembly arranged between the stationary component and rotating component to seal a gap the...
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WO/2021/213735A1 |
The invention relates to an abrasive material (10) comprising a nickel aluminide intermetallic phase, in particular a beta nickel aluminide (β-NiAl) intermetallic phase with a Laves phase, as a matrix (1) for abrasive particles (2). It ...
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WO/2021/209713A1 |
The present invention relates to a housing (130) for a turbine engine turbine (1), the housing (130) extending about an axis (X), comprising an annular wall (112) and a cooling device (100), the wall (112) being provided with at least on...
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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/2021/205099A1 |
A sealing assembly (1) for a turbine engine comprising a first element (2) and a second element (3), the first and second elements (2, 3) being concentric and in relative rotational movement with respect to each other about an axis of ro...
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WO/2021/199992A1 |
A labyrinth seal according to an embodiment of the present disclosure is provided with a first member including a plurality of sealing fins arranged spaced apart in the axial direction, and a second member which faces the first member wi...
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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/2021/200847A1 |
This fin tip position measurement method comprises: a jig installation step for installing a jig having a flat measurement surface expanded in a circumferential direction and an axial direction to a tip of at least one among a plurality ...
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WO/2021/201828A1 |
A rotary machine seal assembly (200) includes seal segments (102) configured to circumferentially extend around a rotor (108) between a stator (106) and the rotor (108) of a rotary machine. One or more seal segments include a shoe plate ...
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WO/2021/199993A1 |
A labyrinth seal according to an embodiment of the present disclosure is provided with a first member, and a second member facing the first member, wherein: the first member includes a plurality of sealing fins which are disposed spaced ...
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WO/2021/191553A1 |
Disclosed is an aircraft turbine engine (10), comprising a gas generator (12) and a fan (14) arranged upstream from the gas generator (12) and configured to generate a gas inlet stream (F), part of which flows into a duct of the gas gene...
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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/2021/191534A1 |
The invention relates to a turbine assembly comprising: a plurality of ring sectors (50) forming a ring (5); a support structure (6) comprising a shroud (60) from which there project radial flanges which serve to hold latching tabs of ea...
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WO/2021/191538A1 |
Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there...
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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/2021/186135A1 |
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/2021/186134A1 |
A turbine assembly (1) comprising: - a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, - a ring support structure (3), comprising an annular shroud (6), and in addition -a plurality of angular spacer sec...
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WO/2021/176167A1 |
The invention relates to a method for manufacturing a composite platform (30) for a fan of an aircraft turbine engine, wherein said platform comprises an elongate wall (32) and is configured to extend between two fan blades (3), said wal...
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WO/2021/176161A1 |
The invention relates to a composite platform (30) for a fan of an aircraft turbine engine, which comprises an elongate wall (32) and is configured to extend between two fan blades (3), said wall comprising an aerodynamic outer surface (...
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WO/2021/176160A1 |
Method for manufacturing a composite platform (30) for an aircraft turbine engine fan, this platform having a wall (32) of elongate shape that is configured to extend between two fan blades (3), this wall having an aerodynamic external f...
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WO/2021/175488A1 |
A urbine (14), and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members (2) and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel (...
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WO/2021/176168A1 |
The invention relates to a method for refitting blade (10, 10a) shrouds (14a) of a rotor wheel in an aircraft turbomachine, the rotor wheel having a disc bearing blades (10; 10a) that each have an airfoil (26) extending between a root an...
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WO/2021/175495A1 |
A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches t...
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WO/2021/170933A1 |
The invention relates to an abradable coating for a turbomachine, comprising a mineral compound having a Mohs hardness of 6 or less and a melting temperature of more than 450 °C or even 800 °C, and a polymeric compound with a content o...
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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/2021/165600A1 |
In order to increase the inertia of a blade sealing lip for an aircraft turbine engine, and thus to improve the lifespan of such a sealing lip, the sealing lip (48) is shaped so as to have a hollow (98) in its outer surface (S2) and a co...
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WO/2021/168269A1 |
A seal element for an annular control device includes an elastomer seal sleeve having an annular opening therein and arranged to be radially compressed to contact an exterior of a pipe disposed within the elastomer seal element. The elas...
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WO/2021/165605A1 |
The invention relates to a turbine comprising a rotor (27) surrounded by a stator, a first movable stage comprising a set of rotary blades, a second movable stage comprising a second set of rotary blades, nozzle guide vanes (33) includin...
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WO/2021/152243A1 |
The invention relates to a casing (3) of an aircraft turbomachine, said casing comprising: - an annular shell (9) extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, - an...
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