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WO/2023/047033A1 |
The invention relates to a high-pressure gas turbine for a turbomachine, the turbine comprising a nozzle guide vane assembly (30), an annular array of moving blades (40) mounted downstream of the nozzle guide vane assembly (30) a bleed c...
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WO/2023/025827A1 |
The invention relates to a sealing ring (1) for a turbomachine, comprising at least a first segment (2) and a second segment (3), each of which segments have a first longitudinal end (4) with respect to a circumferential direction (31) o...
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WO/2023/025520A1 |
The invention relates to a sealing device (1) for a flow machine, wherein the sealing device (1) comprises a flap seal (2), a surface (4), a first protrusion (5) protruding from the surface (4), a second protrusion (6) protruding from th...
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WO/2023/020748A1 |
The invention is about a flat shaped sealing device (01) for sealing a gap between two parts having a sealing length and a sealing width from one side edge (18) to the opposite side edge (19) of at most 0,2-times the sealing length and h...
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WO/2023/012414A1 |
The invention relates to a guide vane assembly (15) for a turbomachine (1) extending about an axis (X) and comprising at least one stator vane (22) which extends from a platform (21), a first flange (23) extending radially inwards from t...
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WO/2023/008060A1 |
A shaft sealing device according to at least one embodiment of the present disclosure comprises: a plurality of thin plates which are disposed in a circumferential direction of a rotating shaft, and which have a width in the axial direct...
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WO/2023/286960A1 |
The present invention relates to a steam turbine, wherein, in order to enable steam, which is collected inward when colliding with an impeller to rotate the impeller, to be transferred to another impeller adjacent thereto to increase the...
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WO/2022/271358A1 |
In a gas turbine engine (100), coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case (132), the nozzle of the turbine (140), and the exhaust diffuser (150). Embodiments of an interface are disclosed...
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WO/2022/263740A1 |
Abradable coating (100) comprising a tubular cell structure, characterized in that the tubular cell structure comprises a fibrous reinforcement of discontinuous short fibres densified by a ceramic matrix.
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WO/2022/258497A1 |
The invention relates to an assembly for a turbine engine (T) fan case (2) and an air inlet (3), in particular for an aircraft, the turbine engine (T) extending along a longitudinal axis (X) and comprising at least one fan (1) mounted so...
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WO/2022/258911A1 |
A rotor wheel (10) for an aircraft turbine engine, said wheel comprising: - a disc (12) having a main axis (A) and provided with cells (14) at its outer periphery, the cells extending along the axis and each comprising a bottom (14a) and...
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WO/2022/248789A1 |
The invention relates to a method for manufacturing an abradable layer and a substrate coated with this layer, comprising the following steps: preparing a powder composition (30) comprising at least ceramic particles and an inorganic fil...
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WO/2022/243628A1 |
The present invention relates to a platform (6) for a fan assembly (1), comprising a flow passage wall (8) extending in an axial direction having an upstream end and a downstream end, and comprising two axial stiffeners (10). The platfor...
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WO/2022/234205A1 |
Method (100) for mounting an annular abradable element (16) in an annular groove of a member (21) of a turbomachine (1), the annular abradable element (16) extending along an axis (A3) and comprising a cellular structure, the groove open...
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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/2022/218735A1 |
Sealing strip element (1) for sealing a gap (5) between two components (2a, 2b) of a gas-turbine installation, and extends along a longitudinal direction (21) and has a contoured cross section in a ribbed central region (10). The sealing...
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WO/2022/208007A1 |
The invention relates to a turbine ring assembly (1) comprising: ring segments (40) made of ceramic matrix composite material and each comprising first and second attachment tabs (42, 43) and a cavity (30) for the circulation of an air f...
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WO/2022/208018A1 |
The invention relates to a turbine (9) comprising a sealing device (18) connected to a nozzle (17) with a radial degree of freedom. The sealing device (18) comprises a reinjection pipe configured to collect a fluid present in a cavity (4...
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WO/2022/210501A1 |
This seal ring manufacturing method, for manufacturing an annular seal ring, involves: a step in which, in a state in which the two ends of a first member and a second member having a semicircular shape have been brought into contact wit...
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WO/2022/204367A1 |
In a method for forming an abradable material (36), the abradable material has at least 20% by volume rutile titania (44) and hBN (46). The method includes: blending a first titania powder having an oxygen debit of at least 5.0% with a s...
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WO/2022/189735A1 |
The invention relates to a stator assembly for an aircraft turbomachine extending about an axis (Al) and comprising: • a shroud ring (41), • a plurality of bladed ring sectors (30), • sliding means allowing relative movement betwee...
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WO/2022/184324A1 |
The system comprises a rotary turbomachine (3), including dry gas seals (9). A seal leak gas collecting line (14) fluidly connects the at dry gas seals (9) to the seal leak gas inlet (15) of the ejector (13). A seal leak gas discharging ...
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WO/2022/180330A1 |
The present application relates to an assembly for a turbine engine (1), comprising a first rotor (2) which is rotatable about a longitudinal axis (X-X) of the turbine engine (1), the first rotor (2) comprising a first arm (26); a second...
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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/2022/180322A1 |
The invention relates to a distributor (30) for a turbine (8) of a turbomachine (1). The distributor (30) comprises a radially internal platform (32), a blade (38) and a base (36) which is covered with a track (37) made of abradable mate...
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WO/2022/166037A1 |
A tip clearance online measuring device (100), comprising: an optical fiber probe (5), configured as capable of producing a conical light beam; an optical fiber (6), connected at one end to the optical fiber probe (5), the optical fiber ...
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WO/2022/167148A1 |
The disclosure concerns a gland condenser skid system comprising a direct contact heat exchanger as gland condenser (20), configured to collect and condensate steam coming from a steam turbine sealing system, wherein the steam turbine se...
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WO/2022/157448A1 |
The present invention relates to a rotor (2) of a turbine extending about a longitudinal axis (X-X'), comprising at least one rotor disc (21) which, at its periphery, supports at least one rotor blade (20), each blade (20) comprising an ...
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WO/2022/155134A1 |
Composite thermal spray powders are formed by manufacturing two or more powder feedstock components having different chemical compositions, particle size ranges and morphologies, these different features arising from different powder man...
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WO/2022/152579A1 |
The disclosure concerns an abrasive gas turbine blade tip cap preform (11) for bonding to a blade tip to form an abrasive blade tip cap, the abrasive gas turbine blade tip cap preform (11) being formed of a bonding layer (12) and an abra...
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WO/2022/146807A1 |
A sensing system and method for detecting wear of an abradable layer on a stationary engine casing is provided. The system is capable of measuring the abradable thickness of the abradable layer by embedding abradable sensor in the abrada...
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WO/2022/139799A1 |
An interposable seal assembly (1) for use between a pair of shafts (8, 9) to separate a first side (11) and a second side (12) is presented. The assembly (1) includes a first ring (2), a second ring (3), an annular member (4), a sealing ...
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WO/2022/129733A1 |
A method (200) for manufacturing a ceramic matrix composite turbomachine blade comprising at least a structural part and a functional part secured to the structural part, the method comprising: • - obtaining an assembly (210) comprisin...
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WO/2022/123157A1 |
The invention relates to a turbine stator assembly (9) comprising a guide vane assembly (17) and a sealing ring (41) bearing an abradable element (26) of a dynamic sealing ring. The assembly comprises pins (60) secured to the sealing rin...
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WO/2022/123148A1 |
The invention relates to a blade (60) and a sealing element (59) forming an assembly for a turbomachine turbine. The blade (60) comprises an airfoil (61) and a platform (62) to which the sealing element (59) is connected. An internal cha...
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WO/2022/123174A1 |
The invention relates to a manufacturing process for producing a turbomachine component (100) comprising an internal cooling circuit (60), wherein a cast intermediate workpiece (10) is provided and all or part of the remainder (50) of th...
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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/2022/123146A1 |
Disclosed is a propulsion unit (100) for an aircraft, this propulsion unit comprising: - a gas generator (102); - an air inlet (110); and - a sealing system (112) inserted axially between the air inlet and the gas generator, characterise...
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WO/2022/113483A1 |
This seal device comprises: a movable seal ring arranged so as to be deformable in the radial direction, in a state of facing an outer peripheral surface of a rotor of a steam turbine capable of rotating around the axis; a first elastic ...
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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/2022/105206A1 |
A multi-thrust-plate gas turbine capable of balancing an axial force, the gas turbine comprising a rotating shaft (1), and a gas compressor (2), a front radial bearing (61), a plurality of thrust plates (11), a thrust bearing (62), a rea...
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WO/2022/106779A1 |
The invention relates to a turbine engine assembly 1 comprising a first rotor element (2) and a second rotor element (3) extending around a longitudinal axis X and coupled to one another by means of a gear coupling (4), the first rotor e...
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WO/2022/105213A1 |
A multi-rotor micro gas turbine comprising an air inlet channel (4), a compressor (1), a combustion chamber (5), a turbine (2), a rotating shaft (3), a free turbine (18), a motor (19), an exhaust passage (7), a free casing (17), a free r...
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WO/2022/099890A1 |
A sealing structure based on a circumferential relative speed, the sealing structure comprising: a sealing head, wherein the sealing head is annular, and protruding annular sealing teeth are formed on the inner circumferential face of th...
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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/2022/091798A1 |
A honeycomb seal provided with a honeycomb structure in which a plurality of hole portions arranged so as to be recessed from a sealing surface are defined by partition walls. The partition wall has a high-strength portion and a low-stre...
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WO/2022/073711A1 |
The invention relates to a bearing (3), to a gas turbine unit (10) having such a bearing, and to a method for operating said gas turbine unit. The bearing (3) has an annular bearing body (21), on the axially opposing end faces of which a...
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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/2022/054777A1 |
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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