| Document |
Document Title |
|
WO/2023/161583A1 |
The present invention relates to blading (25, 26) for a turbomachine (10), comprising: - a blade (31) having an aerodynamic profile; - a platform (32, 33) comprising a flow-path surface (321) intended to delimit a primary flow path (21A)...
|
|
WO/2023/161577A1 |
The invention relates to a nickel-based alloy powder, that comprises in weight percentages, 14.00 to 15.25% of chromium, 14.25 to 15.75% of cobalt, 4.00 to 4.60% of aluminium, 0 to 0.50% of iron, 0 to 0.15% of manganese, 3.00 to 3.70% of...
|
|
WO/2023/161582A1 |
The invention relates to a turbine engine (1) for an aircraft, which turbine engine has a primary annular flow path (10) and a cold stream duct (20, 30) extending around the primary annular flow path (10), said turbine engine comprising:...
|
|
WO/2023/164283A1 |
A fan blade adapted for connecting to a mount includes a body having an airfoil shape in cross-section, the body including a hollow portion having a lower surface and a. solid portion depending from the body to a location below the lower...
|
|
WO/2023/160875A1 |
The variable inlet guide vane device comprises a disc-shaped member and an annular member coaxial to disc-shaped member and forming a unit therewith. A set of variable inlet guide vanes are pivotally mounted between the disc-shaped membe...
|
|
WO/2023/161320A1 |
The invention relates to a stage for a turbomachine compressor, comprising a row of stator vanes (24) extending radially inwards from an outer shroud to an inner shroud (28) housed in a cavity (30) of the rotor (12), and an air recircula...
|
|
WO/2023/161093A1 |
The invention relates to an assembly (1) comprising a machine (2) consisting of a first element (10) coupled to a second element (20), the machine (2) being connected to a chassis (30), the chassis (30) also comprising a guide interface ...
|
|
WO/2023/157344A1 |
A turbine according to the present invention comprises a rotor and a plurality of turbine blades disposed along the peripheral direction of the rotor, wherein: the plurality of turbine blades includes first turbine blades including first...
|
|
WO/2023/156751A1 |
The invention relates to a system for attaching a turbomachine blade, comprising: - a blade comprising, at the blade root, two portions (54, 56) that are separated from one another in a transverse direction X so as to provide a cavity (C...
|
|
WO/2023/156049A1 |
A steam turbine including at least one steam turbine section, wherein said at least one steam turbine section comprises at least two blade stages. Said blade stages include a row of fixed blades and an accompanying row of moving blades t...
|
|
WO/2023/156063A1 |
A nozzle sector for a sectorized annular stator of a gas turbine, comprising an inner platform and an outer platform, said inner platform and said outer platform being substantially concentric with respect to turbine rotational axis and ...
|
|
WO/2023/152440A1 |
The present invention relates to a turbine rotor (1) comprising a rotor disc (2), provided at its periphery with a plurality of axial cells (23) for receiving a bilobed root (30) of a blade (3), each cell (23) comprising a radially inner...
|
|
WO/2023/148443A1 |
The invention relates to a blade (1) made of a composite material, the blade comprising a fibrous reinforcement densified by an organic matrix and being provided, in an attachment zone (4), with a metal element (5), the blade being chara...
|
|
WO/2023/148448A1 |
The invention relates to a vane (4) made of a composite material for an aircraft turbomachine fan, the vane comprising means (8) for measuring internal deformations of the vane and means (9) for remotely storing and transmitting signals ...
|
|
WO/2023/144427A1 |
The present invention relates to an oblong turbine, consisting of a flow compressor for aviation engines, comprising a housing (2) for blades (3) which describe a non-circular path (t) having at least one rectilinear section (a), said ho...
|
|
WO/2023/147119A1 |
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422 defining a plenum 424. An airfoil 402 extends radially inw...
|
|
WO/2023/147116A1 |
Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to enga...
|
|
WO/2023/147117A1 |
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422, wherein the interior platform surface, the forward rail, ...
|
|
WO/2023/138887A1 |
The invention relates to a turbine blade (1, A) with a cover strip (13) or support vane, which has a coating (18) on its upper half, the coating (18) extending at most up to 40% of the radial length of a vane blade (10) of the turbine bl...
|
|
WO/2023/137526A1 |
The present invention provides a heat engine operating on a novel closed thermodynamic cycle. The primary characteristics of the heat engine comprise a boiler, condenser, liquid pump, and a regenerative expander in which heat is recovere...
|
|
WO/2023/139332A1 |
The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a directi...
|
|
WO/2023/138866A1 |
The invention relates to a turbine blade with a blade root (1), each of which has two axial projections (7', 7''; 8', 8'') along a longitudinal axis (30) with radial bearing surfaces (10', 10''; 11', 11'') for bearing against bearing sur...
|
|
WO/2023/140268A1 |
A turbine rotor blade according to at least one embodiment of the present disclosure comprises a blade root in which a first internal passage extending in a blade height direction is formed and a first opening on one-end side of the firs...
|
|
WO/2023/134176A1 |
A gas turbine, comprising a rotating shaft (100), a compressor (200), a turbine (300), and a combustion chamber (400). The compressor (200) and the turbine (300) are sleeved on the rotating shaft (100); a guide vane assembly (600) is pro...
|
|
WO/2023/134983A1 |
The disclosure relates to a turbine blade (1) having an aerofoil (7), wherein the aerofoil (7) extends along a longitudinal axis (50), and having a blade tip (9), wherein, at the blade tip (9), a lower V limb (42) of an element (42, 43) ...
|
|
WO/2023/135375A1 |
The present invention relates to an application head (1) for automatically applying fibres, which application head comprises at least: - an application roller (3) that is designed to apply fibres to a mould (F), which application roller ...
|
|
WO/2023/135336A1 |
The invention relates to a method for reconstructing a metal part (100) made of Inconel 713 superalloy by means of metal additive manufacturing, implementing a direct metal deposition (DMD) technique using focused energy, wherein a powde...
|
|
WO/2023/131452A1 |
A Ni based NiCoCrAlY coating comprising: Cobalt (Co) 24.5% - 26.5% Chrome (Cr) 14.5% - 16.5%Cr Aluminum (Al) 11.6% - 12.6% Yttrium (Y) 0.3% - 0.5% Iron (Fe) 4.0% - 5.0% Tantalum (Ta) 0.6% - 0.8% Molybdenum (Mo) 0.4% - 0.6% Silicon (Si) 0...
|
|
WO/2023/127211A1 |
This rotor blade comprises: a blade body extending in a blade height direction that is a direction perpendicular to an airfoil cross-section; and a platform that is provided to an end at a hub side, from between a tip side and the hub si...
|
|
WO/2023/121968A1 |
A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned betwe...
|
|
WO/2023/117131A1 |
The invention relates to a turbo machine with a shaft, an impeller arranged on said shaft, an inlet channel (222) configured to guide operating fluid to said impeller, and an outlet channel (224) configured to guide operating fluid from ...
|
|
WO/2023/121680A1 |
A filter for an airfoil of a vane of a turbomachine is disclosed. The filter includes a mounting member for mounting to an endwall of the vane. The mounting member has a first flow exit opening defined therethrough for fluid communicatio...
|
|
WO/2023/118720A1 |
The invention relates to an aerodynamic element (28) of a turbomachine comprising a body (32) extending in a radial main direction and a radial end (34, 60) located at a radial end of the body (32), the aerodynamic element (28) further c...
|
|
WO/2023/118687A1 |
The invention relates to a part (105) comprising a substrate (10) made of ceramic matrix composite material, said substrate being coated with a multilayer stack comprising at least, and in this order, starting from the substrate: - a tie...
|
|
WO/2023/121488A1 |
A method includes positioning a constraining member (150) on a component (100) to create a zone (155) between the component (100) and the constraining member (150). A first material composition (170) is positioned in the zone between the...
|
|
WO/2023/122009A1 |
Disclosed herein is a composite co-fiber comprising a plurality of ceramic tows; one or more sacrificial yarns; where the sacrificial yarns are operative to undergo dissolution, decomposition or melting upon being subjected to an elevate...
|
|
WO/2023/118712A1 |
The invention relates to a part made of coated composite material, comprising: - a substrate made of composite material having a ceramic matrix; - a tie-coat layer covering the substrate; and - a protective coating that is on the tie-coa...
|
|
WO/2023/111433A1 |
The invention relates to a turbomachine (10) for an aircraft comprising a stator (16), a turbine shaft (17) and an electric machine (18) arranged to the rear of the turbine shaft, and comprising an electric machine stator (22) and an ele...
|
|
WO/2023/113102A1 |
The present invention relates to a rotor assembly having a protective core. The rotor assembly according to an embodiment of the present invention comprises: a disc which is inserted in a rotary shaft and has a plurality of insertion gro...
|
|
WO/2023/111454A1 |
The present invention relates to a turbine rotor (2) of a turbine engine of an aircraft, the rotor comprising a rotor disc (3) provided at its periphery with a plurality of cavities (30) for receiving the root (42) of a blade (4). This r...
|
|
WO/2023/105155A1 |
The invention relates to a method for producing a bladed component (10) for an aircraft turbine engine, this bladed component (10) comprising a blade (12) which has a stacking axis (X) and at least one longitudinal end of which is connec...
|
|
WO/2023/106125A1 |
A turbine blade comprises a blade body, a plurality of cooling passages extending in the blade height direction inside the blade body and connected to each other via folded portions, and a bypass portion that is provided in a partition w...
|
|
WO/2023/105162A1 |
The present invention concerns a metal powder for an additive manufacturing method, the metal powder comprising a nickel-based alloy comprising between 0.02% and 0.04% of carbon, between 18% and 22% of chromium, between 11% and 13% of co...
|
|
WO/2023/105150A1 |
The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4...
|
|
WO/2023/105176A1 |
The invention relates to a method for manufacturing a part made of SiC/SiC composite material, the method comprising: • producing a fibrous preform from silicon carbide fibres; • depositing an interphase onto the fibres the fibrous p...
|
|
WO/2023/099832A1 |
The invention relates to a method (100) for manufacturing a blade, the method comprising preparing (102) a spar preform arranged in a first mold, the spar preform comprising a core and a root; a first injection step (104) of injecting a ...
|
|
WO/2023/099022A1 |
A manufacturing process for the synthesis of environmental barrier coating system (EBC) which protect Si-based Ceramic Matrix Composite (CMC) material against oxidation and volatilization at high temperatures is disclosed. The manufactur...
|
|
WO/2023/099856A1 |
The invention relates to an assembly comprising a disk (2) of a moving gear of a turbomachine comprising an axis of rotation and teeth (21, 21'). The teeth each comprise a first lateral surface (21a) on one side and a second lateral surf...
|
|
WO/2023/099098A1 |
Disclosed is a method for selectively removing a ceramic coating from adjacent cooling pockets of a turbine blade. In said method, a high-speed water jet is used to at least partially remove ceramic material from at least one pocket (7) ...
|
|
WO/2023/099117A1 |
The invention relates to a device comprising an asymmetrical wing profile (2) and an adjusting device (15), which asymmetrical wing profile (2) has a profile thickness (q) and a profile chord (p) extending between a wing leading edge (n)...
|
