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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/2021/191521A1 |
Method for manufacturing a metal component (1), characterized in that it comprises the following steps: a shell (2) made of a titanium-based material is provided, the shell (2) having a first surface (3) and a second surface (4) remote f...
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WO/2021/191523A1 |
The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air ...
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WO/2021/191544A1 |
A turbine rotor blade (100, 300) made of ceramic matrix composite material comprising at least a blade profile (101, 201, 301) and a blade root (102, 302) present at a longitudinal end of the blade profile, characterized in that it compr...
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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/2021/191559A1 |
The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nos...
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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/2021/191531A1 |
The invention relates to a fibrous texture (100) intended to form the fibrous reinforcement of a blade (10) of a turbine engine (1) made of composite material which has a three-dimensional weave between a plurality of warp threads or str...
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WO/2021/191528A1 |
Turbofan engine (10) of longitudinal axis (X-X') comprising a primary duct (20), in which there flows a primary flow (F1) at a primary pressure (P3), and a secondary duct (19), which radially surrounds said primary duct (20) and in which...
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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/2021/186896A1 |
This composite-material blade formed by using a fiber-reinforced resin containing a resin and reinforcing fibers is provided with: a base material part provided on the inner surface of the composite-material blade; and a first cover part...
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WO/2021/186122A1 |
The main object of the invention is a turbine blade (18) of a turbine engine, comprising a platform, a vane, a cooling cavity supplying a plurality of cooling outlets (25), which are arranged along the trailing edge (BF), and two radiall...
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WO/2021/185544A1 |
The invention relates to a method for adapting a turbine assembly which is designed for a first operating parameter range, in particular load range, to a second operating parameter range, in particular load range, in which method - a tur...
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WO/2021/186121A1 |
Blade (18) for a turbine (7) of a turbomachine having a cooling zone (ZF) comprising three different types of cooling orifices (25, 26, 27) that are formed through the wall of the airfoil (30) and that are spaced apart from one another r...
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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/2021/187016A1 |
This composite material blade, which is formed using a composite material including reinforcing fibers and resin, and which has a positive pressure surface and a negative pressure surface, is provided with a ventral part, being the part ...
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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/2021/186124A1 |
The invention relates to a method for chemical pickling of a cast metal part, comprising a metal enclosure which defines an inner space in which at least one porous ceramic core is housed, and an outer space, the ceramic core being in fl...
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WO/2021/185942A1 |
According to the invention, by selecting elements of a cobalt-based alloy with silicon, a weldable cobalt-based alloy with high strength is provided.
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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/2021/181031A1 |
The invention relates to a fan module (100) for an aircraft turbomachine (10), comprising: - a fan (14) comprising a disc (32a) carrying fan blades (30), - a rotor (62a) of an electric machine (62), this rotor (62a) having an annular gen...
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WO/2021/176164A1 |
The present invention relates to a method for coating a ceramic matrix composite part with an environmental barrier, in which a first powder comprising a rare earth silicate and a second powder comprising boron are sintered.
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WO/2021/176162A1 |
The invention relates to a fibrous texture (100) intended to form the fibrous reinforcement of a turbine engine (1) blade (10) made of composite material, the texture being in a single piece and having a three-dimensional weave between a...
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WO/2021/175538A1 |
Improved cooling is made possible by an improved cooling structure with cooling air holes (18) inside a depression (20) in a blade tip (3) and a special arrangement of multiple cooling air holes (25) which are supplied by a single coolin...
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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/2021/176179A1 |
The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in ...
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WO/2021/175879A1 |
The invention relates to a method for cleaning the surface of components (1) consisting of ceramic fiber composite materials (2) for applying an environment-stabilized protective layer (4'), and to a method for applying an environment-st...
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WO/2021/170780A1 |
The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150)...
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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/2021/170952A1 |
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/2021/170294A1 |
A rotary machine assembly (1) for a turbomachine, such as a rotor, is disclosed. The rotary machine assembly (1) comprises a rotor wheel (2) where a plurality of circumferentially spaced female dovetail slots (21) are obtained. The rotar...
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WO/2021/170254A1 |
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.
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WO/2021/171043A1 |
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.
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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/2021/164958A1 |
There is disclosed a fixing apparatus (10) for fixing a secondary component (14) to a fan blade, the fixing apparatus comprising: a first clamp part (16) comprising a first inner surface (20) and a second clamp part (18) comprising a sec...
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WO/2021/166757A1 |
A turbine blade comprising: a platform; an airfoil part that extends from the platform in a blade height direction, and has a pressure surface and a suction surface extending between a front edge and a rear edge; a blade root part that i...
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WO/2021/164988A1 |
The invention relates to a method for the additive manufacture of a platform structure (10) for a turbine blade (50), or a ring segment of a turbomachine (60), comprising: - a) providing a geometry of the platform structure (10), wherein...
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WO/2021/165604A1 |
The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geom...
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WO/2021/160969A1 |
The present invention relates to a shaft (15) for a propulsion system (1) configured to rotate a reducing mechanism (12) about a rotational axis (X), the shaft (15) comprising: - a first end (16) configured to engage with an input gear (...
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WO/2021/160951A1 |
The invention relates to a fibrous texture (10) for forming the fibrous reinforcement of a vane of a turbine engine from composite material, comprising a zone (24) of reduced rigidity with warp threads made from second fibres having an e...
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WO/2021/160961A1 |
A vane (46) for a turbine engine comprises a body (54) in the shape of an airfoil formed of a shell (56) made of a composite material formed of a three-dimensional textile of reinforcing fibres consolidated by a hardened resin, the shell...
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WO/2021/160383A1 |
The invention relates to a rotor blade (1) for a flow machine, comprising a blade airfoil region (2) and a blade root region (3), the rotor blade (1) having at least one fiber composite part (4) made of fiber composite material, and an e...
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WO/2021/156562A1 |
The invention relates to a turbomachine part (20), comprising: (i) a substrate (21) of a nickel-based superalloy, comprising from 5.0 to 8.0 wt.% of cobalt, 6.5 to 10 wt.% of chromium, 0.5 to 2.5 wt.% of molybdenum, 5.0 to 9.0 wt.% of tu...
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WO/2021/156564A1 |
The invention relates to a turbomachine part (20) having a nickel-based superalloy (21) comprising 5.0 to 8.0 wt.% of cobalt, 6.5 to 10 wt.% of chromium, 0.5 to 2.5 wt.% of molybdenum, 5.0 to 9.0 wt.% of tungsten, 6.0 to 9.0 wt.% of tant...
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WO/2021/156577A1 |
The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), ...
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WO/2021/156559A1 |
Disclosed is a rotor vane (10) for an aircraft turbine engine, this vane comprising a blade (16) extending between an inner platform (19) and an outer platform (20) which carries at least one projecting lip (31, 32), the blade having a l...
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WO/2021/152233A1 |
Disclosed is a one-piece fibrous preform (100) obtained by three-dimensional weaving comprising a first skin (110), a second skin (120) and a longitudinal stiffening portion (130) connecting the skins, the portion forming a stiffening el...
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WO/2021/153531A1 |
Provided is a turbine rotor blade having a suction-side fillet portion which comprises: a central fillet portion positioned at the center of the length of the suction-side fillet portion along a direction in which the suction-side fillet...
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