| Document |
Document Title |
|
WO/2023/247903A1 |
A bladed assembly (40) for a turbomachine comprises a plurality of blades (42) distributed around an axis (28) and each comprising a vane (44) and a platform (46) formed at a free end of the blade (42). The platform (46) of each blade co...
|
|
WO/2023/247855A1 |
The invention relates to a bladed turbomachine assembly extending around an axis (AX), this turbomachine comprising a disk carrying blades (21a-21d), wherein each blade (21a-21d) extends radially from a root through which it is rigidly a...
|
|
WO/2023/247906A1 |
The invention relates to a pitch change mechanism (70) comprising a frame (72), an actuating cylinder (74) having a moving part (102) capable of translating relative to the frame (72), and a linkage system (78) connecting the moving part...
|
|
WO/2023/247856A1 |
The invention proposes a turbomachine bladed assembly (10) comprising at least two adjacent blades (12), each blade (12) comprising a radial vane (14) and a platform (16) located at a free radial end of the vane (14), wherein the platfor...
|
|
WO/2023/241450A1 |
Provided is a turbine guide vane structure. The structure comprises a CMC component and a metal cover plate. The CMC component comprises a blade body and an edge plate, the edge plate being matched with the metal cover plate. At least pa...
|
|
WO/2023/242707A1 |
A turbine blade (1), in particular the blade of a turbine engine or a gas turbine, comprises a locking portion (2) and an airfoil (3) with a uniform structure, in which there is at least one pocket (4) filled with powder. In the at least...
|
|
WO/2023/242523A1 |
The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement and a matrix. The fiber reinforcement includes a plurality of plies that are each formed of warp yarns a...
|
|
WO/2023/242522A1 |
The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement and a matrix. The fiber reinforcement includes a plurality of plies that are each formed of warp yarns a...
|
|
WO/2023/242524A1 |
The disclosed fan blade is composed at least in part of a structure (50) made of composite material comprising a fiber reinforcement (62) and a matrix (64). The fiber reinforcement (62) includes a plurality of plies (66, 68) that are eac...
|
|
WO/2023/243512A1 |
A cooling air passage of a rotor blade has: a main passage into which cooling air can flow; a plurality of leading ejection holes that can eject the cooling air from a leading edge in the blade surface; and a plurality of film holes that...
|
|
WO/2023/242490A1 |
One aspect of the invention relates to a device (30) for axially retaining a moving blade (10) of a low-pressure turbine in a recess (21) of a rotor disc of axis (X) of the turbine. This device comprises a stop part (40) intended to exte...
|
|
WO/2023/237834A1 |
The invention relates to a coating method comprising a step of forming a tie coating (200) on a surface of a substrate (100), and a step of forming a barrier coating (300) on the tie coating (200). The tie coating (200) is formed by chem...
|
|
WO/2023/232028A1 |
A turbine guide vane mounting structure, comprising an upper cover plate, a lower supporting plate and a turbine guide vane located between the upper cover plate and the lower supporting plate. The turbine guide vane comprises an upper e...
|
|
WO/2023/233096A1 |
The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interio...
|
|
WO/2023/233114A1 |
The invention relates to a titanium alloy comprising, as contents by weight: - 4.0% to 5.0 % of aluminium; - 3.50% to 4.50% of tin; - 1.0% to 4.0% of zirconium, - 2.0% to 5.25% of molybdenum; - 1.0% to 2.50% of niobium; - 0.10% to 0.25% ...
|
|
WO/2023/234946A1 |
A stator vane assembly defining a chordwise direction and a crosswise direction perpendicular to the chordwise direction is provided. The stator vane assembly includes: an attachment plate; and an attachment assembly coupled to the attac...
|
|
WO/2023/233110A1 |
The invention relates to a method for manufacturing a part made of ceramic matrix composite material, comprising at least: a step of infiltrating a fibrous structure (400) by dipping a portion of said fibrous structure in a bath (6) of t...
|
|
WO/2023/233092A1 |
The invention relates to a blade comprising: - a blade body (12) having an aerodynamic profile comprising a first fibrous reinforcement obtained by three-dimensional weaving and comprising a first matrix in which the first fibrous reinfo...
|
|
WO/2023/227860A1 |
A method of designing a blade row of a turbomachine is provided, comprising providing design parameters defining the blade row to a mistuning model. The mistuning model predicts aeroelastic performance of the blade row from the design pa...
|
|
WO/2023/227833A1 |
A turbine wheel (100), a gas turbine (200) and a method for cooling a turbine wheel (100) are presented. A turbine wheel (100) has a rotation axis (5), a first side (110) and a second side (120), said sides (110, 120) being opposite side...
|
|
WO/2023/222549A1 |
The invention relates to a de-icing system configured to be mounted on a surface (3A, 3B) of a mechanical part (1) to be de-iced, said system comprising at least: - a piezoelectric actuator (9), - a fastening device (11) configured to fa...
|
|
WO/2023/223741A1 |
A turbine blade according to one embodiment comprises: a first internal passage extending in a blade height direction and opening at the root of the blade; a second internal passage that extends in the blade height direction, that is for...
|
|
WO/2023/205270A1 |
The present invention is directed to wind turbine blades that include an additive manufactured system-integrated tip. The disclosed wind turbine blades reduce the levelized cost of electricity (LCOE) for both new and existing wind turbines.
|
|
WO/2023/202901A1 |
The present method refers to a method of servicing a continuous flow engine. Herein, the method makes use of an improved evaluation of the planning of a scheduled servicing to ensure the reliability of such continuous f low engine and im...
|
|
WO/2023/200454A1 |
Turbomachine and method for assembling/disassembling a rotor structure of the turbomachine are disclosed. A plurality of impeller bodies is supported on a tie bolt. Threadingly connecting a first coupling nut with the tie bolt to axially...
|
|
WO/2023/198980A1 |
The invention relates to a stator part (20) comprising a platform (22), a first blade (24), a second blade (26), and a fin (28) having a leading edge (30) and a trailing edge (32), the fin extending opposite an upper surface (124) of the...
|
|
WO/2023/199725A1 |
This method for constructing a thermal barrier coating according to at least one embodiment of the present disclosure comprises a step for forming a topcoat layer on a bond coat layer formed on a heat-resistant alloy base material of a t...
|
|
WO/2023/198981A1 |
The invention relates to a stator part (20) of a turbine engine, comprising a platform (22), a blade (24, 26) extending radially relative to a central axis (A), and a fin (28) extending radially from a fin root (44) to a fin tip (46), th...
|
|
WO/2023/197976A1 |
The present invention relates to the technical field of single crystal superalloys, and in particular to a Ni3Al-based single crystal superalloy, and a preparation method therefor and an application thereof. The present invention provide...
|
|
WO/2023/198979A1 |
The invention relates to a turbine engine motor having an unducted fan, the motor comprising a plurality of guide vanes (10) made of composite materials. Each of the guide vanes is intended to be fixed only to an inner fixed structure (2...
|
|
WO/2023/196523A1 |
A first turboexpander generator defines a portion of a first conduit flow passage. The first turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the first turboexpander generato...
|
|
WO/2023/194676A1 |
The invention relates to a blade (10) for an aircraft turbomachine, the blade comprising a platform (16) and at least one airfoil (12) attached to the platform via a curved connection interface (14), the airfoil (12) comprising a leading...
|
|
WO/2023/196520A1 |
A system includes an electric generator, a power electronics system, a first heat exchanger, and a second heat exchanger. The electric generator includes a turbine wheel, a rotor, and a stator. The turbine wheel is configured to receive ...
|
|
WO/2023/196522A1 |
A system includes an electric generator, a power electronics system, and a heat exchanger. The electric generator includes a turbine wheel, a rotor, and a stator. The turbine wheel is configured to receive process gas and rotate in respo...
|
|
WO/2023/196077A2 |
A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine includes a first side piece having a first outer surface, a second side piece having a secon...
|
|
WO/2023/184799A1 |
An aero-engine turbine assembly, comprising a turbine assembly body and a cooling assembly, wherein the turbine assembly body is provided with an internal runner, and comprises a turbine moving disc (4), a blade end wall (5) and a turbin...
|
|
WO/2023/187674A1 |
A turbomachine, comprises a case (2) and a rotor (4) positioned in the case (2) so that it can rotate with respect to the case (2) around its own longitudinal axis (X-X). The rotor (4) comprises: one blading located on the rotor (4) and ...
|
|
WO/2023/187297A1 |
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner e...
|
|
WO/2023/187296A1 |
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner e...
|
|
WO/2023/180672A1 |
The present invention relates to a coated part (1) intended to be mounted in a turbomachine, comprising: - a substrate (3) made of composite material with an at least partially ceramic matrix, and - an environmental barrier (12) on the s...
|
|
WO/2023/174577A1 |
The invention relates to a rotor blade (30) in a gas turbine engine (50) characterized by a coating (10) on a blade tip (20) of the rotor blade (30) comprising an oxidation resistant abrasive layer (11) and the rotor blade tip (20) havin...
|
|
WO/2023/175822A1 |
This TiAl alloy vane wheel is made of a TiAl alloy and installed in a vehicular turbocharger. The TiAl alloy has a lamellar structure in which an α2 layer containing Ti3Al and a γ layer containing TiAl are alternately laminated. The Ti...
|
|
WO/2023/175281A1 |
Method for locating a mark (46, 48) on a casing (10) of a turbomachine (1) of an aircraft, characterized in that it comprises: a) a step of visually inspecting the arms (16), the outer surface (12a) of the internal shroud (12) and the in...
|
|
WO/2023/175265A1 |
The present invention relates to an aircraft part comprising: a composite material structure comprising a fibrous reinforcement embedded in a matrix; a heating element (9) configured to heat the part, the heating element (9) being embedd...
|
|
WO/2023/175266A1 |
The present invention relates to a nickel-based superalloy, characterized in that its composition comprises or advantageously consists essentially of, in percent by weight of the total composition: Al 2.5 - 3.8, Co 7.9 - 16.9, Cr 9.7 - 1...
|
|
WO/2023/176577A1 |
A method for applying a thermal barrier coating according to one embodiment includes a step for forming a topcoat layer on a bond coat layer formed on a heat-resistant alloy substrate of an object. In the step for forming the topcoat lay...
|
|
WO/2023/175256A1 |
The invention relates to a method for maintaining a bladed wheel of a high-pressure turbine of a turbomachine, extending along an axis, comprising a disc (11) comprising cavities (15), and blades (12) extending radially and each comprisi...
|
|
WO/2023/169725A1 |
The invention relates to a rotor disk (1) comprising a slot (2) for receiving a blade foot (77) of a turbine blade, wherein the slot (2) has multiple indentations (20', 20'',...) along the longitudinal axis (30) of the slot for protrusio...
|
|
WO/2023/170497A1 |
The invention relates to a reversible turbomachine comprising : - a rotor housing containing one or more rotor members which rotor comprises a plurality of mutually spaced discs which rotate about a rotational axis and are coaxially disp...
|
|
WO/2023/161576A1 |
The invention relates to a titanium-based alloy powder which comprises, in percentages by weight, 32.0 to 33.5% aluminium, 4.50 to 5.10% niobium, 2.40 to 2.70% chromium, 0 to 0.1% iron, 0 to 0.025% silicon, 0 to 100 ppm carbon, 0 to 100 ...
|
