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WO/2024/018049A1 |
The invention relates to an assembly (4; 40) for a turbine engine (1) comprising a wall (6) having a guide surface (8) for guiding an air flow (F1) and a row of stator vanes (10; 100) extending from the wall and arranged annularly about ...
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WO/2024/017385A1 |
A movable blade of a high-pressure turbine. A cooling unit is provided in the movable blade, and has cooling chambers which are in communication with an inner chamber via an impact hole. The cooling unit comprises at least one series-con...
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WO/2024/012897A1 |
Repair method of components of continuous flow engines The present invention refers to an improved method of repairing a continuous flow engine component utilizing an automatic system. Furthermore, the present invention refers to an insp...
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WO/2024/012682A1 |
The invention relates to an oxide-fiber reinforced oxide ceramic composite material the surface of which is coated with at least two electrically conductive layers.
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WO/2024/015249A1 |
A system to passively control heat for automobiles comprising: a turbo shield configured to protect components within an engine bay of a vehicle; a mesh screen positioned over the turbo shield, wherein the mesh screen is configured to pa...
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WO/2024/001379A1 |
Disclosed in the present invention is a blade dimension chain modeling method taking tenon-mortise connection into consideration, which relates to the technical field of assembly deviation analysis of aircraft components. The method comp...
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WO/2024/000855A1 |
A gyroscope assembly, a turbine blade, an impeller, and a wind power generator set. The turbine blade comprises a blade body (10), a web (11), and a gyroscope assembly. The blade body (10) has an inner cavity; the web (11) is fixedly dis...
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WO/2024/004529A1 |
This gas turbine stator blade is provided with: a leading edge part partition that divides a cavity inside the blade into a leading edge side cavity and a trailing edge side cavity; a negative pressure surface side partition wall that is...
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WO/2024/002212A1 |
An anti-spin blade, comprising a forward sweep centre of gravity stacking section, a trailing edge stacking section and a transition section, the forward sweep centre of gravity stacking section being formed by stacking along a forward s...
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WO/2023/247879A1 |
The invention relates to a method (100) for producing a plurality of blades (10) of height (Ha), which comprises: providing a mould (30) comprising an internal cavity bounded by an internal side face (34) of the mould which is axisymmetr...
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WO/2023/247097A1 |
Method of making a turbine blade with a passage comprising the following steps: - Providing a first part 4.1 and a second part 4.2; - Machining the first part 4.1 and the second part 4.2 in order to form the profile of the first and the ...
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WO/2023/247857A1 |
The invention proposes a bladed assembly (10) comprising two adjacent blades (12), and each blade (12) a platform (16) located at a free radial end, wherein the platform (16) of the first blade (12) comprises a lateral face (18) which is...
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WO/2023/250173A1 |
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles di...
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WO/2023/249757A1 |
A pneumatically variable nozzle vane (200) is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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% ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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.
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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