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Patent Searching and Data


Matches 51 - 100 out of 23,809

Document Document Title
WO/2021/060093A1
In a turbine blade (1) provided with a cooling passage (11) configured such that a cooling medium (CL) travels from a root portion side to a tip end portion side in a blade height direction (H), and a lattice structure (21) in which a pl...  
WO/2021/055200A1
A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickne...  
WO/2021/048484A1
Fibrous preform for a composite blade and also a composite blade formed by means of such a preform, a rotor and a rotating machine comprising such a blade, the preform comprising a first longitudinal section (51), configured to form a bl...  
WO/2021/048508A1
The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to prov...  
WO/2021/045841A1
Embodiments of the present disclosure generally relate to protective coatings on substrates and methods for depositing the protective coatings. In one or more embodiments, a method of forming a protective coating on a substrate includes ...  
WO/2021/044022A1
The invention relates to a method for selecting a radial profile of a cavity to be produced in a rear side of an impeller. The selection method advantageously allows the radial profile (16C) of a cavity (14) to be adapted to a specific a...  
WO/2021/044098A1
One aspect of the invention concerns a method for relieving the residual stresses in a part (10) having a step of increasing the speed of rotation comprising: a first sub-step of measuring, at a first given instant ( t Δ), a value ( vA2...  
WO/2021/045645A1
A device for bleeding air in the rotor of a turbojet engine compressor consists of air bleed slots, and air bleed tubes for guiding cooling air into a turbine, wherein the air bleed tubes are provided with ledges and with an upper angle-...  
WO/2021/044107A1
The present invention concerns a turbomachine hub, intended to be mounted so as to be able to rotate about a longitudinal axis (X) of the turbomachine, the hub comprising a main body (1) arranged around the longitudinal axis (X), an oute...  
WO/2021/045920A1
A closure element for an internal passage in a component, and a related method and turbine blade or nozzle are disclosed. The closure element includes a spherical body made of a first superalloy, and a plurality of extensions extending f...  
WO/2021/037296A1
The present invention relates to a rotor blade for a compressor, which rotor blade has a blade airfoil (10). The blade airfoil has a pressure side (Ps), a suction side (Ss) and a blade tip (11). The blade tip (11) has at least one channe...  
WO/2021/040919A1
A damped turbine blade assembly (490, 491, 492, 493) for a gas turbine engine (100) is disclosed. The damped turbine blade assembly (490, 491, 492, 493) includes a damper (495, 496, 497, 498) positioned within a first small slot (481a) o...  
WO/2021/041192A1
The present application provides a control stage for a steam turbine. The control stage may include a number of guide blades and a number of runner blades. The number of runner blades may define a ratio of a pitch to a width of about 0.7...  
WO/2021/039090A1
This high-frequency hardening apparatus is provided with: an induction heating coil which has a U-shaped part that sandwiches a turbine blade, a pair of linear parts, and a connection part connecting the U-shaped part and the linear part...  
WO/2021/038173A1
The invention relates to a blade (3) of a fan (1) of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement (4) obtained by means of the three-dimensional weaving of strands and a matrix in...  
WO/2020/263419A3
A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the...  
WO/2021/041055A1
A support fixture for a wind turbine blade that enables rotation of the blade about its longitudinal axis, and which includes a conformal insert. A selectively deployable stacking frame portion is provided. The support fixture is interch...  
WO/2021/038848A1
The present invention is an integrally bladed rotor manufacturing method in which blades are machined, with high precision, by cutting. The integrally bladed rotor manufacturing method according to the present invention is a method for m...  
WO/2021/034327A1
A component (68) formed of a three-dimensional ceramic matrix composite material (CMC) is provided. The component (68) includes a first wall and a second wall that intersects the first wall at an angle such that the intersection forms a ...  
WO/2021/030249A1
A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine componen...  
WO/2021/028225A1
Embodiments of bladed rotors· and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors comprises providing a workpiece comprising a first rotor blade segment. The first rotor blade segm...  
WO/2021/028628A1
The invention relates to a method for coating a turbomachine part (1), comprising the deposition of a paint by electrophoresis on the turbomachine part, the voltage between the part and a counter-electrode (20) being controlled during th...  
WO/2021/028637A1
The invention relates to a method (500) for verifying the conformity of the aerodynamic profile of an actual blade of an aircraft turbine engine with respect to a theoretical blade, which comprises: - constructing (521) a skeleton curve ...  
WO/2021/025524A1
Disclosed are an impulse turbine and a turbine device. The disclosed impulse turbine includes a cylindrical body having an axial hole, and a blade unit arranged to surround the circumference of the body. The blade unit includes a cylindr...  
WO/2021/026345A1
An airfoil includes a multi-part body and one or more thermally conductive pins. The multi-part body has an interior region and is formed from multiple pieces joined with each other at an interface. The pieces have multiple cavities and ...  
WO/2021/023927A1
Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for...  
WO/2021/021231A1
A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a...  
WO/2021/020518A1
This steam turbine is provided with: a rotary shaft; a plurality of movable blades each of which has a movable blade body (42) and a shroud (43), and which are circumferentially arranged at intervals; a casing (5) that has a recessed sec...  
WO/2021/018333A1
The invention relates to a module (20) for a turbomachine (1), having two components (21, 22), which each extend peripherally and are segmented, wherein the components (21, 22) have an axial overlap (40) and have a radial offset (41) rel...  
WO/2021/018882A1
The invention relates to a turbine impeller (10) of an exhaust-gas turbine (61) of a turbocharger (50) and a turbocharger (50) having a turbine impeller (10) of this kind for an internal combustion engine, wherein the turbine impeller (1...  
WO/2021/019170A1
A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall (16), an upper surface wall (17), a leading edge (14) and a trailing edge (15) and comprising a plurality of internal ventil...  
WO/2021/019156A1
The invention relates to a turbomachine moving blade (2) comprising at least one cooling circuit comprising at least one cavity (16; 16a, 16b) extending radially between the foot and the vertex, at least one air intake opening at a radia...  
WO/2021/021232A1
A blade for a gas turbine includes a removed portion space, and further includes an airfoil portion defining the removed portion space, the airfoil portion formed from a base material, and a replacement component formed to fill the remov...  
WO/2021/015861A1
A gas turbine engine having a pre-swirler (400) adjustability is presented. The pre-swirler includes a pre-swirler insert (420) installed in a component enclosed by a cover (12, 16). The component includes an inner compressor exit diffus...  
WO/2021/013920A1
The present invention relates to a method for continuously manufacturing an abradable sealing element (4), this element comprising a support substrate (40a, 40b) covered by a coating comprising at least two successive layers, each compri...  
WO/2021/013281A1
The invention relates to a rotor blade (20) to be arranged in a gas conduit (3) of a turbomachine (1), having a rotor blade airfoil (23), which radially inwardly has a chord length Si, radially outwardly has a chord length Sa, and in a r...  
WO/2021/013280A1
The invention relates to an intermediate element (10) for a blade/rotor disc connection in a rotor of a turbomachine, in particular in a rotor of a power plant, the intermediate element (10) being adapted to the shape of a blade root (30...  
WO/2021/013282A1
The invention relates to a rotor blade (20) for arranging in a gas channel (3) of a turbomachine (1), comprising a rotor blade sheet (23) which has a leading edge (23a) and a trailing edge (23b) downstream therefrom with respect to a flo...  
WO/2021/013279A1
The present invention relates to an integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse body housing (40; 40') is fastened by means of ...  
WO/2021/009157A1
A method of bonding a composite vane (1) to at least one support (2). The method comprises the steps of positioning an end of a vane (1) within a support (2), causing an adhesive to flow between the vane and the support from an inlet (3)...  
WO/2021/008816A1
The invention relates to a turbine casing for an exhaust-gas turbine, which turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the ci...  
WO/2021/008842A1
A blade for a turbomachine fan, the blade (1) being made from a composite material containing a plurality of longitudinal conductive fibres (F) embedded in an electrically non-conductive matrix, the blade (1) having at least one fastenin...  
WO/2021/008901A1
A shaft connection (50) comprises: a female component (51) with an internal spline toothing system (52), and a male component (55) with an external spline toothing system (56) which can be brought into engagement with the internal spline...  
WO/2021/008815A1
The invention relates to a blade ring (2) for an axial turbomachine, comprising a blade support (6) with a number of holding grooves (8) for rotor blades (10), said grooves running in the axial direction (A), and a corresponding number o...  
WO/2021/005286A1
Disclosed is a process for manufacturing a fibrous preform for a part made of composite material, comprising creating a fibrous texture (200) by three-dimensional or multilayer weaving between a plurality of weft layers (202) and of warp...  
WO/2021/005312A1
The present invention relates to a blower vane (1) of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement (11) and a matrix in which the fibrous reinforcement (11) is embedded. The va...  
WO/2021/007055A1
A method for creating a three-dimensional (3D) mark in a protective coating including at least one of a TBC and a bond coating over a metal part, is provided. The method may include positioning a mask over the protective coating, the mas...  
WO/2021/004821A1
The solution proposed relates in particular to an engine component (3), having at least one first loading zone (33), which is designed for dynamic loads arising on the engine component (3) when the engine component (3) is correctly built...  
WO/2021/001611A1
A fibrous reinforcing structure for a part made of composite material woven as a single piece by three-dimensional or multi-layer weaving between a plurality of layers of weft filaments (202) and a plurality of layers of warp filaments (...  
WO/2020/260258A1
The invention relates to a structural assembly for a gas turbine engine (10), which structural assembly comprises a fan (23) and a forked fan shaft (7), which is coupled to the fan (23) and comprises a radially outer fan shaft (71) and a...  

Matches 51 - 100 out of 23,809