| Document |
Document Title |
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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.
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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)...
|
|
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 ...
|
|
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 ...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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.
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
WO/2022/049064A1 |
The invention relates to a rotor assembly (RA), especially for a gas turbine, comprising at least a first rotor disc (FRD) and a second rotor disc (SRD), the two rotor discs (FRD, SRD) are arranged directly next to each other, wherein th...
|
|
WO/2022/051760A1 |
A guide vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil extending between the inner platform and the outer platform. The vane airfoil has a bow shape. A first outer seal slot and a second ou...
|
|
WO/2022/051101A2 |
A gas turbine blade including a root for connecting to a rotor of a gas turbine, a platform attached to the root defining a side surface and a groove formed in the side surface, and an airfoil including a metallic substrate extending fro...
|
|
WO/2022/045989A1 |
An underwater power generation turbine with airfoil cross-section embodiment used for generating more power from currents such as sea, river, irrigation canals etc. characterized in comprising; turbine blade (5) of spiral structure and i...
|
|
WO/2022/043060A1 |
The invention relates to a rotor assembly (RA) comprising: at least a first and a second rotor disk (RD1, RD2), a number of through holes (TH) in the second rotor disk (RD2) which extends co-axially to the rotational axis (RX), a set of ...
|
|
WO/2022/046146A1 |
A turbine blade in a gas turbine engine includes an airfoil extending in a radial direction. The airfoil has an outer wall delimiting an airfoil interior. The outer wall includes a pressure sidewall and a suction sidewall joined at a lea...
|
|
WO/2022/038323A1 |
Blower vane (1) for an aircraft turbine engine, the vane comprising a blade (13) connected to a root (11), the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium ...
|
|
WO/2022/038070A1 |
The invention relates to a method for producing a coating (1) on at least part of the surface of a component (10) of high-temperature-resistant ceramic fibre composite materials for protection from environmental influences, and to a comp...
|
|
WO/2022/035460A1 |
A gas turbine engine includes a compressor section, a combustor section, a turbine section, a hot gas path and a layered component (600) including a substrate (502) and a thermal barrier coating (TBC) (602) having: a single layer of 6-15...
|
|
WO/2022/029377A1 |
The present invention relates to a method for producing a structure by an additive manufacturing technique implementing chemical vapour deposition assisted by focused energy radiation, including the formation of a reinforcement that comp...
|
|
WO/2022/032296A1 |
Flow control devices and structures for turbomachines. In some examples, the flow control devices and structures include various arrangements of flow guiding channels, partial height vanes, and other treatments located on one or both of ...
|
|
WO/2022/022780A1 |
The invention relates to a guide vane (10) for arrangement in a gas duct (14) of a turbomachine (1), said guide vane comprising a guide vane blade (11) and an outer platform (12) and being arranged radially outside on the guide vane blad...
|
|
WO/2022/022773A1 |
The invention relates to a rotor clamping composite (10) of a turbomachine, in particular a rotor, said composite being secured against rotation, comprising at least two composite components (11) which are arranged one behind the other i...
|
|
WO/2022/026115A1 |
A coated article (20;60) includes a substrate (22) and a coating (24;62) on the substrate. The coating includes at least a first layer (30). The first layer has: a matrix (50); and a filler (52) at 2.0% to 40% by volume in the first laye...
|
|
WO/2022/025867A1 |
A method of repairing a component using an additive manufacturing process is presented. The method includes submerging the component into a powder bed so that a portion of the component to be repaired is level with a surface of the powde...
|
|
WO/2022/018197A1 |
A method (190) for manufacturing a vaned component (100) of a turbomachine is provided. The method includes providing a base portion ( 115), additively manufacturing, on top of the base portion (115), a plurality of vanes (150) and a plu...
|
|
WO/2022/018555A1 |
A turbine (3) for a spirometer (1) comprises a hollow tubular body (5) containing a rotor (12) which is mobile around a longitudinal axis (K) of this tubular body (5) and two deflectors (11) placed at an intake opening (7A) and at an out...
|
