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WO/2023/007098A1 |
The invention relates to an aeronautical propulsion unit comprising a central engine (3), an upstream series and a downstream series of blades (9, 6), the blades (90, 60) of at least one of these series being adapted to be driven in rota...
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WO/2023/007073A1 |
A method for manufacturing a part made of ceramic matrix composite (CMC) material comprises: - producing a fibrous preform from silicon carbide fibres; - consolidating the fibrous preform by gas-phase chemical infiltration; - injecting a...
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WO/2023/001629A1 |
The invention relates to a turbine disc (14) for a turbine and to a method for producing a turbine disc (14), whereby efficient turbine discs (14) can be produced in a particularly inexpensive manner. This is achieved in that a turbine d...
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WO/2023/285668A1 |
The invention relates to a method (100) for supporting treatment of damage to blading of a turbomachine (10) having a plurality of blades (11), comprising the following steps: determining (103) a treatment contour (202) for mechanically ...
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WO/2023/281205A1 |
The invention relates to a nickel-based superalloy comprising in percentages by mass: 5.0 to 6.5% of aluminum, 0.50 to 2.5% of tantalum, 1.50 to 4.0% of titanium, 0 to 7.0% of cobalt, 12.0 to 16.0% of chromium, 0.50 to 2.5% of molybdenum...
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WO/2023/281221A1 |
The invention relates to a fire safety system (30) for a turbomachine (1), such as an aeroplane turbofan or a turboprop engine, the turbomachine comprising at least one turbine (3) having a turbine disc (5) and an annular cavity (16) whi...
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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/2023/275459A1 |
A vane (20) for an aircraft turbomachine, said vane comprising a blade (21) and a cooling circuit (28) inside the blade, said cooling circuit (28) comprising at least one longitudinal flow cavity (58) of a cooling air stream (RF), the co...
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WO/2023/275456A1 |
One aspect of the invention relates to a foil (1, 1') and a root (21, 21') of a blade (2, 2') of a turbomachine rotor and comprises: - a base (17), - two side limbs (12) that are connected to each other by the base (17), at least the fir...
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WO/2022/269158A1 |
A nickel-based superalloy comprises in weight percentages: 5.4 to 6.0% of aluminium, 7.5 to 9.0% of tantalum, 0.10 to 0.25% of titanium, 5.5 to 7.5% of cobalt, 4.0 to 5.5% of chromium, 0.10 to 0.70% of molybdenum, 4.0 to 5.0% of tungsten...
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WO/2022/269180A1 |
Disclosed is an impeller for a fan module of a jet turbine engine, the impeller comprising a plurality of blades (16) made of composite material, each blade (16) having a root (16A) assembled with a base (18) that is separate from the ba...
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WO/2022/269174A1 |
A method for manufacturing a blade (10) made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield (14) is attached to one edge of an airfoil, said shield having a gener...
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WO/2022/269177A1 |
The invention relates to a nickel-based superalloy comprising in weight percentages: 5.0 to 6.0% of aluminium, 6.0 to 9.0% of tantalum, 1.0 to 5.0% of cobalt, 5.0 to 7.5% of chromium, 0 to 1.0% of molybdenum, 4.0 to 6.0% of tungsten, 0.5...
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WO/2022/269173A1 |
The invention relates to a method for manufacturing a blade (26) of a fan (12) for an aircraft turbomachine (10) extending around a longitudinal axis (X), the blade (26) comprising an aerofoil (28) made of a composite material having a l...
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WO/2022/263743A1 |
The invention relates to a fibrous preform (10) for a guide vane of a gas turbine engine, wherein the preform (10) comprises two fibrous portions (14) forming an airfoil of the vane and defining therebetween an interior volume (16), and ...
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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/2022/258257A1 |
A rotor assembly (70) for a gas turbine engine (10), the rotor assembly (70) comprises a rotational axis (20), a disc (36) and at least one blade (38). The disc (36) comprises at least one slot (72), the slot (72) has at least one pair o...
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WO/2022/258932A1 |
The present disclosure relates to a method for manufacturing discs for turbomachines, the method comprising: obtaining a nickel-based alloy powder; shaping the powder in order to obtain a disc; characterised in that the step of obtaining...
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WO/2022/254648A1 |
This shaping apparatus comprises a beam emission unit capable of emitting an energy beam, and a material supply unit capable of supplying a shaping material to an irradiation position of the energy beam, wherein a cover member is joined ...
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WO/2022/248804A1 |
The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and ha...
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WO/2022/243619A1 |
The invention relates to equipment (100) for treating an annular component (10) of an aircraft turbomachine, having: a support (110) of elongate shape along an axis (X), the support comprising, at one of its ends, a mount (111) configure...
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WO/2022/243375A1 |
The invention describes a method for balancing turbine wheels (10) of exhaust gas turbines, and a balanced turbine wheel (10). An exhaust gas turbine wheel has a hub rear wall (15) facing away from the fluid flow region and having a rece...
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WO/2022/238051A1 |
The invention relates to a turbine rotor (1) having an improved rotor tip (7), which has at least one cooling channel (48, 57) in the rotor blade (8), said cooling channel (48, 57), in the region of its cuspidal point (43, 51), having at...
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WO/2022/238770A1 |
A method for designing a turbine blade includes receiving initial geometrical and aerodynamic information of the turbine blade, obtaining the maximum amount of stress within a determined area of maximum stress, and obtaining a safety fac...
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WO/2022/234229A1 |
The invention relates to a process for manufacturing a turbomachine blade, wherein: - a part (4) is manufactured comprising a foot (4), a heel (6) and an air stream zone (10) extending between the foot and the heel, the air stream zone c...
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WO/2022/235076A1 |
The present invention relates to a gas turbine blade comprising: an airfoil-shaped blade housing; and a squealer tip extending from the edge part of the tip surface which is the end cross section of the blade housing, wherein the squeale...
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WO/2022/228727A1 |
The rotor comprises a plurality of rotor segments arranged axially adjacent to one another. A tie rod extends through the rotor segments. Opposed first and second locking members arranged at the axial ends of the tie rod lock the rotor s...
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WO/2022/227583A1 |
A turbine blade, comprising a blade body (1), which comprises a blade root, a blade tip, a leading edge and a trailing edge. The pressure surface of the blade body is provided with first air film holes (11), the leading edge of the blade...
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WO/2022/232107A1 |
Methods for welding materials such as superalloys, hard-facing materials, and aluminides that are difficult to weld without cracking. Instead of welding one layer at a time on the weld surface like existing methods, the weld comprises st...
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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/2022/224009A1 |
The present invention describes a turbocompressor (1) comprising at least one rotor (10) the axis (11) of which comprises at least one preloading element (60) permanently maintaining the diameter of the axis larger than its natural diame...
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WO/2022/222225A1 |
The present application relates to the technical field of high-temperature alloys, and in particular to a high-temperature alloy having low stacking fault energy, a structural member and an application thereof. The high-temperature alloy...
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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/2022/214320A1 |
An aerofoil for a gas turbine engine comprises a suction side wall, a pressure side wall, a leading edge (215) and a trailing edge (216). The suction side wall (212) and the pressure side wall (213) extend from a first end to a second en...
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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/2022/214630A1 |
The invention regards a method of manufacturing a component, the method comprising the steps of; providing an additively manufactured component, providing a housing having the component, filling the housing having the component with a fi...
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WO/2022/217273A1 |
A turbine blade (200) tip shroud (220) has a first cutter tooth (260) extending from a tip rail (250) from one of the upstream side (252) and the downstream side (254) of the tip rail (250) and adjacent the leading edge (229) of the body...
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WO/2022/208004A1 |
The invention relates to a nickel-based superalloy comprising in weight percentages: 5.5 to 7.5% of aluminum, 1.0 to 4.0% of tantalum, 0.50 to 3.0% of titanium, 3.0 to 7.0% of cobalt, 8.0 to 12.0% of chromium, 0 to 2.5% of molybdenum, 0 ...
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WO/2022/208000A1 |
One aspect of the invention relates to a foil (300) for a turbomachine rotor blade (10), configured to be mounted on a root (20) of the rotor blade and comprising a general U-shaped cross section formed by two lateral branches (302) conn...
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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/2022/208002A1 |
The present invention relates to a vane (7) of a turbine engine, comprising: - a structure which has an aerodynamic profile (20); - a spar (21) comprising a vane root portion (24), a blade portion (25) arranged inside the structure which...
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WO/2022/208861A1 |
A heat-resistant alloy member comprising: a heat-resistant alloy substrate; Re-based, W-based, or Cr-based multipurpose alloy layer provided on the surface thereof in a region that comprises at least a region where thermal insulation sho...
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WO/2022/199990A1 |
The invention relates to an additively manufactured material structure (10) for a turbine component (20, 30), in which the material structure (10) comprises a solid material lattice (11) and a porous functional material (12), the functio...
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WO/2022/201926A1 |
This turbine comprises: a rotor blade body having a blade root fixed to a rotational shaft that extends along an axis, a base section provided integrally to the radial-direction outer-side of the blade root, a blade body provided integra...
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WO/2022/201932A1 |
This turbine comprises a turbine rotor, a turbine casing, a plurality of turbine rotor cascades, a plurality of turbine stator cascades, and a diffuser which forms an exhaust gas flow path through which exhaust gas flows from one side in...
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WO/2022/195192A1 |
The invention relates to a turbomachine part (1) comprising a central core (2) made of a pitted rigid material which comprises a first face and a second face opposite the first face, characterized in that the central core (2) is surround...
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WO/2022/189033A1 |
The present invention relates to a method for applying a strain tolerant oxide coating on a substrate, the strain-tolerant oxide comprising zirconia or zirconate as main component, characterized in that the strain tolerant oxide is appli...
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WO/2022/189256A1 |
The invention relates to a micro-turbomachine, consisting of a whole rotor assembled from a plurality of partial shaft elements, the assembled whole rotor being supported in gas and/or air bearings (2), which micro-turbomachine is charac...
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WO/2022/189236A1 |
The invention relates to an additive repair system (1) and to a method for determining correction parameters of a corresponding system (1). The additive repair system (1) comprises a construction platform (2) having a construction volume...
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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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