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WO/2022/180340A1 |
A turbine (1) for a turbomachine of longitudinal axis (X), comprising: an alternating arrangement of annular rows of movable blades (64) and of fixed blades (65) and a radially inner annular cavity (68) formed radially inside the movable...
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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/2022/180322A1 |
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/2022/176805A1 |
A turbine blade and a rotating machine, wherein provided are: a blade (31); a hollow section (41) that is provided in the blade (31); and a low-melting-point metal (42) that is filled into the hollow section (41).
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WO/2022/177452A1 |
An article includes a base portion (12) including a cast iron with the cast iron having a first fatigue strength; at least one groove (16) formed in the base portion: and a filler metal (34) disposed in at least one groove of the at leas...
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WO/2022/171240A1 |
The present invention relates to a method for producing a flow structure (20) for a turbomachine (1), in which method a blade (22) is joined at a first end (31) to a main body (21), which blade (22) has, in a portion (34) distal from the...
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WO/2022/171950A1 |
The invention relates to a turbomachine component such as a blade, comprising a wall that is provided with at least one cooling orifice (26) having a metering portion (32) and a widened diffusion portion (33). According to the invention,...
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WO/2022/171957A1 |
The invention relates to a method for repairing an end plate of a turbomachine rotor, said end plate comprising a crown (16) having at least two collar fastening holes (19) and at least one balancing-weight fastening hole located between...
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WO/2022/171727A1 |
The invention relates to a propulsion system (1) for an aircraft, which propulsion system comprises a rotor (2; 2b; 2c) having a rotor main body (4-4c) and rotor blades (3; 3b; 3c) attached to the rotor main body (4-4c), wherein air can ...
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WO/2022/171955A1 |
Turbomachine guide vanes assembly (10) extending about an axis (70) and comprising blading (20) mounted between an outer shroud (42) and an inner shroud (30), and a position-maintaining device (60) configured to be arranged in an elastic...
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WO/2022/171946A1 |
Assembly (1) comprising a body (10) extending around a central axis (X-X), the body (10) having an outer surface (14) from which a plurality of blades (20) extend, each of the blades (20) having a blade root (22) and a blade tip (24) def...
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WO/2022/168262A1 |
A blade member having a groove structure formed on a surface, wherein the groove structure comprises a plurality of first groove structures, a plurality of second groove structures, and a third groove structure. The plurality of first gr...
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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/2022/156509A1 |
The present invention provides a process treatment method for frequency mixing and sorting of blades, being capable of avoiding a scrapping phenomenon caused due to the overlarge size difference of the blades caused because frequency mod...
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WO/2022/159930A1 |
An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is disclosed. The apparatus can include: an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured...
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WO/2022/159708A1 |
An environmental barrier coating topcoat for improved resistance to calcium-magnesium-aluminosilicate (CMAS) degradation is disclosed. The CMAS mitigation compositions are based on spinel-containing materials. A CMAS-resistant multilayer...
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WO/2022/157097A1 |
The invention relates to a sandblasting mask (50) and to the use thereof for sandblasting blade tips in a method comprising: a step of positioning a plurality of sandblasting masks (50), each blade passing through an opening (58) in a ma...
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WO/2022/157445A1 |
The invention relates to a method for manufacturing a preform (15) for a turbomachine component with a weaving installation comprising at least a first delivery roll (36) and a storage roll (34), the method comprising the following steps...
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WO/2022/152994A1 |
The invention relates to a propulsion assembly (200) for an aircraft comprising a double-flow turbomachine (1) equipped with a fan (15), an aerodynamic outer casing (5) forming a nacelle, and a mounting pylon, the propulsion assembly hav...
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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/2022/148928A1 |
Stator assembly for straightening an air flow, turbojet engine, turbofan engine and aircraft, the assembly comprising a plurality of stator vanes distributed around an axis of revolution of the stator assembly, wherein for each stator va...
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WO/2022/150300A1 |
A thermal spray material that exhibits improved thermal conductivity and solid particle erosion resistance is provided for thermal barrier coatings. The thermal spray material forms a thermally stable coating when thermally sprayed. The ...
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WO/2022/144312A1 |
The present application provides an impellor (100) for an air compressor. The impellor comprises an impellor disc (101) and a plurality of blades (103) evenly arranged on the impellor disc in the circumferential direction of the impellor...
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WO/2022/132347A1 |
During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blade...
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WO/2022/126241A1 |
Sacrificial inserts for use in gas turbine engines to reduce friction and wear damage between compressor fan blades and the fan rotors are disclosed. The consumable metallic shims have low friction and reduce fretting and galling on fan ...
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WO/2022/128354A1 |
The invention relates to a blade component (50), a compressor or turbine stage of a gas turbine, in particular a gas turbine engine (10), characterized in that the blade component (50) comprises at least two structural elements (51, 52) ...
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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/2022/128144A1 |
The invention relates to a method for coating a substrate surrounding a gas turbine blade, comprising the following steps: In a first step, a MCrAIY matrix is applied by means of a PVD method; in a further step, an oxide layer is applied...
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WO/2022/129749A1 |
Guide vane assembly (100) for a turbomachine, comprising: an inner platform (102) and an outer platform (101); a plurality of vanes (110) positioned between the inner and outer platforms, the vanes being made of a composite material comp...
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WO/2022/129503A1 |
A method for providing CAM manufacturing instructions for the powder-bed-based additive manufacturing of a component (10) is specified. In this case, a geometry of the component (10), comprising a solid material region (B), a transition ...
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WO/2022/129734A1 |
The invention relates to a blade made of composite material comprising a fibrous reinforcement and an at least partially ceramic matrix, the blade being characterized in that the fibrous reinforcement comprises a first structural portion...
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WO/2022/123177A1 |
Method for manufacturing a turbomachine blade (11) comprising a pressure-side wall (14) and a suction-side wall (15) spaced apart from one another, said blade (11) comprising a tip (S) with: • - a bottom wall (18) extending from the pr...
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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/2022/125075A1 |
Method of forming or repairing a part with an overhung section. The method may include removing a portion, and adding a section to the part. The section includes the overhung section. The adding includes sequentially layering at least on...
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WO/2022/125076A1 |
Method of forming or repairing a part with an overhung section. The method may include removing a portion, and adding a section to the part. The section includes the overhung section. The adding includes sequentially layering at least on...
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WO/2022/117962A1 |
Disclosed is a method for manufacturing a composite material blade (10) for a turbomachine, in particular an aircraft turbomachine, the blade (10) comprising a metal shield (1) extending along a leading edge (12a) of the aerofoil (12), t...
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WO/2022/117931A1 |
A method for manufacturing a fixed turbomachine vane made of a composite material, the method comprising: - forming, by three-dimensional or multi-layered weaving, a fibre blank which is separated over its thickness into first, second an...
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WO/2022/118500A1 |
Provided is a blade capable of optimizing outflow angle in substantially the entirety of the hub region and the tip region, particularly in the blade-end-side hub region and the blade-end-side tip region. The blade is composed of a bas...
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WO/2022/117938A1 |
The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a t...
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WO/2022/112678A1 |
The invention relates to a woven fibrous preform (1) for a hollow aerodynamic profile of a turbomachine blade, comprising a separated trailing edge and the draping of two 3D woven fibrous textures.
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WO/2022/115019A1 |
A turbine (10) configured to operate in a thermodynamic cycle comprising a working fluid circuit, wherein the turbine comprises an impeller (11) mounted on a first end (20a) of a turbine shaft (20), the impeller being arranged in a housi...
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WO/2022/112684A1 |
One aspect of the invention relates to a method for manufacturing a dual-material turbine engine disc, comprising the following operations: providing a rough bore made of a first material, mounting the rough bore about an axis of rotatio...
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WO/2022/112683A1 |
The invention relates to a fibrous texture (11) for reinforcing a turbomachine blade made as a single piece and forming at least the preform of the airfoil profile (10) of the blade and the platform element (24 28).
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WO/2022/105823A1 |
Blade edge plates (6, 7, 8), a blade ring (100), an impeller disk, and a gas turbine engine. The blade edge plate (7) comprises a pair of side edges (71, 72) and a pair of bottom edges (73, 74); in the extension direction thereof, the fi...
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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/2022/106780A1 |
The invention relates to a part (10) made of composite material, in particular for an aircraft turbine engine, comprising: - a body (40) produced from fibres (41) woven in three dimensions and immersed in a resin, in particular an organi...
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WO/2022/106134A1 |
Nickel based super alloy, which comprises at least, especially consists of (in wt%): Iron (Fe) 1.5% - 6.5% especially 3.5% – 5.5% Chrome (Cr) 12.0% - 14.0% Molybdenum (Mo) 1.0% - 2.0% Wolfram (W) 2.0% - 5.0% Aluminum (Al) 5.2% - 5.8% T...
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WO/2022/107467A1 |
Provided is a steam turbine member that suppresses adhesion of scales over a long period of time without impairing the corrosion resistance or the like of a turbine. The present invention provides: a steam turbine member including a ha...
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