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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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WO/2022/107734A1 |
A rotation unit constituent member (1), which is a constituent member of a gas turbine (GT) engine, is provided with: a rotation unit constituent member body (15) that is made of metal; and a hard particle layer (17) that includes a larg...
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WO/2022/108740A1 |
Embodiments of the present disclosure generally relate to protective coatings on aerospace components and methods for depositing the protective coatings. In one or more embodiments, an aerospace component containing a protective coating ...
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WO/2022/106237A1 |
Disclosed is a main shaft (1) for an aircraft turbine engine drive line (A) extending longitudinally from front to rear along an axis (X) and comprising a rear portion (10) configured for receiving a front portion (20) of a rear shaft (2...
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WO/2022/106774A1 |
Disclosed is a composite blade for a turbomachine, in particular an aircraft turbomachine, this blade comprising an aerofoil (12) having a pressure side and a suction side connected together by a leading edge (12a) and by a trailing edge...
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WO/2022/106772A1 |
The invention relates to a blade comprising a shield (14) attached to the upstream end of the body of the blade, the shield (14) comprising an upstream end forming a leading edge of the blade, the shield (14) further comprising a nose (1...
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WO/2022/101277A1 |
Turbomachine, comprising a shaft (10) with a first end and an impeller (20) arranged at and coupled to the first end of the shaft (20), arranged together to rotate about an axis of rotation (1). The turbomachine comprises a friction ring...
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WO/2022/097085A1 |
A gas turbine (1) comprises a disc (10), at the periphery of which a plurality of blades (20) are mounted and extend radially from said disc. Each blade comprises a neck (21) adapted to be coupled to a peripheral zone of the disc, an air...
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WO/2022/096814A1 |
Disclosed is an aircraft turbomachine (10) having a longitudinal axis (A) and comprising: a high-pressure body, termed HP body, a low-pressure body, termed LP body, a fan (48), and a reduction gear (36) having an epicyclic gear train; th...
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WO/2022/096211A1 |
The bonding capacity of a ceramic coating system (16) is improved by adapting the coating parameters such as size of the powder and changing of the parameters of the spraying system.
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WO/2022/096212A1 |
An adhesion promoter layer is produced by means of a novel composition with a lower cobalt content in an MCrAlY alloy, wherein said adhesion promoter layer leads to a very slow growth of the TGO. The nickel-based alloy comprises at least...
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WO/2022/096813A1 |
A set of shafts (34, 72) for an aircraft turbomachine, this set comprising: a first shaft (72) having external splines (76) oriented parallel to an axis of rotation (A) of the shaft, a second shaft (34) having internal splines (74) compl...
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WO/2022/090643A1 |
A fairing element (33) is intended to be placed in a fluid flow passage (F), to surround an obstacle (31) which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairi...
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WO/2022/090664A1 |
The invention relates to a method (100) for fabricating a turbomachine engine blade made from a ceramic matrix composite material comprising a blade and a platform, producing (102) a first fibrous preform, the first fibrous preform formi...
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WO/2022/090654A1 |
The invention relates to a device (30) for pressurizing a turbomachine downstream enclosure (20), said device (30) being fed by means of a pressurizing air flow and comprising: a first shaft portion (9a), a second shaft portion (9b) coup...
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WO/2022/094527A1 |
Methods of forming a desired geometry at a location on a superalloy part (100) are disclosed. The method may include directing particles of a powder mixture (110) including a low melt temperature superalloy powder (112, 114) and a high m...
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WO/2022/084611A1 |
The invention relates to a turbofan engine (1) comprising a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes (10) extending in the secondary duct, downstream of a fan (2), at least one servo extending ...
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WO/2022/084615A1 |
The present invention relates to a blade (3) of a fan (1), made of composite material, of a turbomachine. On a portion (15) of the blade (7) which extends from a lower limit (16) located at a predetermined distance (d) from the shank (6)...
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WO/2022/080094A1 |
This gas turbine blade comprises a platform part having a cooling passage formed inside, and a wing body part protruding from the upper surface of the platform part. A plurality of first ejection ports that eject a gas supplied from the ...
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WO/2022/079360A1 |
The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener (9) defining a well (10) for receiving a blade root (7), and a clamping device (32) for clamping the blade root (7) against the fastener ...
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WO/2022/078727A1 |
The invention relates to a radial turbine (20). The radial turbine (20) comprises: - a turbine housing (21) having a radial gas inflow channel (22); - a nozzle ring (23), which is disposed in the radial gas inflow channel (22); and - an ...
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WO/2022/079370A1 |
The invention relates to a blade (16) comprising a blade body (18) made of a fibre-reinforced organic matrix composite material and a leading edge shield (20) made of a material having better point impact resistance than the composite ma...
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WO/2022/076288A1 |
The present disclosure provides compositions, articles thereof, and methods of forming compositions. In at least one aspect, a composition includes (1) an epoxy, (2) an amino or amido hardener, (3) a polyaniline, (4) a dopant selected fr...
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WO/2022/074314A1 |
The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps: - installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the ...
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WO/2022/069814A1 |
The invention relates to a method for manufacturing a hollow CMC part using a hybrid core (1) comprising an inner portion (10) and a coating (12) made of carbon, silicon or silicon alloy.
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WO/2022/069845A1 |
The invention relates to a turbine blade (60) for a turbine engine, comprising an aerofoil (61) and a platform (62). The platform (62) comprises an internal channel (80) having a suction opening (81) which opens on a first surface (71) o...
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WO/2022/069812A1 |
The invention relates to a method for producing a workpiece (1) having improved resistance to oxidation and high-temperature corrosion, comprising at least the formation of an environmental barrier coating (7) on an at least partially ce...
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WO/2022/067311A1 |
A method for generating material test samples for conducting material tests of a legacy steam turbine rotor having an inter-blade region rotor surface, and an inlet region rotor surface adjoining the inter-blade region rotor surface. The...
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WO/2022/066471A1 |
A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes ...
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WO/2022/063475A1 |
The invention relates to a method for repairing a damaged leading or trailing edge region (2) of a metallic turbine blade (1), which has a suction-side blade wall (3), a pressure-side blade wall (4) and a leading edge (5) and a trailing ...
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WO/2022/057654A1 |
The use of a low-thermal-diffusivity low-frictional-coefficient low-thermal-conductivity low-thermal-expansion silicon nitride glass composite material in an engine, wherein the silicon nitride glass composite material comprises glass po...
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WO/2022/053753A1 |
The present invention relates to a fan blade (1) of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement (4) obtained by three-dimensional weaving of strands (12, 14) and a matrix in which t...
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WO/2022/054561A1 |
A turbine wheel according to at least one embodiment of the present invention is connected to a rotary shaft so as to rotate about the axial line, and comprises, in a cross-section along the axial line, a hub having a hub surface incline...
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WO/2022/055865A1 |
The invention refers to an integral or monolithic nozzle segment (30) having airfoils (33) According to an aspect of the invention a steam turbine has a casing (17) supporting multiple nozzle segments (30) forming a diaphragm (22) with t...
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