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Patent Searching and Data


Matches 301 - 350 out of 23,809

Document Document Title
WO/2020/046396A1
An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the a...  
WO/2020/043989A1
The invention relates to a tool for producing festoons and attachment holes of a disc flange (10) by electrochemical machining using an electrolyte, the tool comprising: an annular support plate (52) for receiving the disc; lower protect...  
WO/2020/043996A1
The invention relates to a turbomachine blade comprising: a blade body made of fiber-reinforced organic matrix composite material, the blade body having an intrados and a head provided with an apex; an erosion protection film (22) which ...  
WO/2020/043980A1
Method for manufacturing a turbomachine composite part, such as a fan blade, this part comprising a fibrous structure which comprises a three-dimensional fibrous preform coated with a surface fibrous web, and which is embedded in a polym...  
WO/2020/046379A1
A cooling channel arrangement for a region of a gas turbine engine is provided. The arrangement includes a cooling channel 26 having cooling sections 34, 36, 38 adapted for use in a component 24 with various component regions 28, 30, 32,...  
WO/2020/043379A1
The invention relates to a radial compressor rotor (RCR), in particular for a geared compressor (GTC), comprising: a shaft (SH) which extends along an axis (X), at least one impeller (IMP1, IMP2) designed with an axial intake and a radia...  
WO/2020/046359A1
There is provided a hybrid component including a metal core (102); a shell (104) comprising a ceramic matrix composite material about the metal core (104); and one or more cavities (106) defined between the metal core (102) and the shell...  
WO/2020/046381A1
A method for manufacturing a heat transfer design for progressive htc cooling channel arrangements for a region of a gas turbine engine is provided. The 5 method includes generating a non-transitory computer-readable three-dimensional (3...  
WO/2020/046158A1
The present invention provides a coolable airfoil section (1) of a turbine component, wherein the coolable airfoil section (1) comprising two sidewalls (2, 3) that are joined at a leading edge (4) and a trailing edge (5). The leading edg...  
WO/2020/043988A1
The invention concerns a method for shaping, by compacting, a fibrous structure (200) obtained by three-dimensional or multilayer weaving between a plurality of layers of warp threads and a plurality of layers of weft threads. The thread...  
WO/2020/040971A1
A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 an...  
WO/2020/041027A1
A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately -0.067 to +0.101 inches, where the X and Y values are in...  
WO/2020/040747A1
A modular casing manifold for cooling fluids of a gas turbine engine is presented. The modular casing manifold has an annular shape including an axial inner plate (211), an axial outer plate (212), a radial forward plate (210) and a radi...  
WO/2020/040967A1
A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 an...  
WO/2020/039142A1
The invention relates to an assembly for a turbomachine (1) extending about an axis (X) comprising: - an inner annular platform (13) and an outer annular platform (14) delimiting a flow channel (3) for a flow flowing from upstream to dow...  
WO/2020/039072A1
A method, device and system of estimation fatigue life of a technical system are disclosed. The method includes computing a lifing probability distribution for at least one component of the technical system based on material property sca...  
WO/2020/039690A1
This blade and gas turbine are provided with a stationary blade main body (22) provided internally with cavities (46, 47), and an inner shroud (23) which is linked to an end portion, in the longitudinal direction, of the stationary blade...  
WO/2020/041072A1
A turbocharger for an internal combustion engine is provided, where the turbocharger includes a housing, a shaft, a turbine wheel, and a compressor wheel. The shaft is rotatable with respect to the housing and defines a centerline. The t...  
WO/2020/036713A1
In a method for repairing a coated article, the article has: a ceramic matrix composite (CMC) substrate; and a coating system having a plurality of layers. A damage site at least partially penetrates at least one of the layers. The metho...  
WO/2020/036050A1
A two-phase flow turbine provided upon a hub coupled to a rotating shaft and driven by receiving two-phase flow including a liquid phase component and a gas phase component. This rotor blade comprises: a rotor blade main body fixed to th...  
WO/2019/194860A3
A component (10) is disclosed having an outer surface (22) of a ceramic matrix composite material (12), wherein the outer surface (22) is part of a thermal protective layer (24) that is 10-50% of a total 3D CMC thickness. The component f...  
WO/2020/035348A1
The invention relates to an outlet guide vane (2) for an axial compressor extending along a rotor axis (x), comprising an airfoil (4) extending in a span direction from a radially inner end (12) at 0% height to a radially outer end (14) ...  
WO/2020/029531A1
A turbine blade (100) having a composite specially-shaped slotted gas film cooling structure. The turbine blade (100) has a hollow structure, and an outer wall (101) thereof has multiple recessed first slots (105). A bottom portion (500)...  
WO/2020/032964A1
A turbine blade airfoil portion having a total length and fixedly attached to a base includes a first portion extending from the base to a repair line such that the first portion has a first length that is shorter than the total length, ...  
WO/2020/030873A1
The invention concerns a mechanical assembly for the transmission of axial forces between two rigidly connected parts, at least one of these parts having an external thread portion (15), said assembly further comprising a nut with intern...  
WO/2020/025902A1
The invention concerns a method for the surface treatment of a component (1), for example a turbomachine component, the component comprising a surface to be treated, the method comprising the following steps: loading a first dispenser (2...  
WO/2020/025406A1
The invention relates to a rotor of a gas turbine, comprising two adjacent rotor disks (01, 06) having a plurality of blade-holding grooves (02) for receiving rotor blades, distributed around the periphery thereof, and comprising an axia...  
WO/2020/027822A1
In one embodiment, an airfoil (36) includes an airfoil body portion (37), an airfoil tip portion (43) disposed radially outward of the airfoil body portion (37), an airfoil root portion (49), and a plurality of radial cooling passages (5...  
WO/2020/025878A1
A method for manufacturing a part made from composite material having a matrix that is at least mainly ceramic comprises: - producing a fibrous structure (100) by three-dimensional or multilayer weaving; - shaping the fibrous structure i...  
WO/2020/027823A1
A hot gas path component assembly includes a first component portion 37 which includes a first set of interlocking features 56B, a second component portion 43 which includes a second set of interlocking features 56A mechanically coupled ...  
WO/2020/025324A1
A method for connecting or joining superalloys is specified. The method comprises a) providing a first part to be joined (1) and a separate second part to be joined (2), wherein the first and second parts to be joined respectively compri...  
WO/2020/025635A1
The invention relates to a turbine (1) that has a housing (101) and a module (13, 15) which is arranged in the housing (102) and has a multistage design and which has an impeller assembly and a diffuser assembly. The diffuser assembly ha...  
WO/2020/021192A1
The invention relates to a turbine blade (13) for a turbomachine, comprising a turbine blade airfoil (14) extending radially, said turbine blade airfoil (14) having a leading edge (16) axially upstream and a trailing edge axially downstr...  
WO/2020/023007A1
The gas turbine engine includes a rotor disk 120 having circumferentially distributed disk grooves 122 and turbine blades 140. Each turbine blade 140 includes a blade root 144 inserted into the blade mounting section 124 of the disk groo...  
WO/2020/020508A1
The invention relates to an additive manufacturing method for components (10) to be used in the hot gas path of turbomachines. The method comprises selectively irradiating a base material (P) for the component (10) with a laser or electr...  
WO/2020/021200A1
The invention relates to a stage of blades (16) with a longitudinal axis (X) intended to be mounted in a turbomachine compressor (10), comprising an annular row of movable blades (12) which are arranged upstream of an annular row of stat...  
WO/2020/023005A1
The gas turbine engine includes a rotor disk (120) having circumferentially distributed disk grooves (122) and turbine blades (140). Each turbine blade (140) includes a blade root (144) inserted into the blade mounting section (124) of t...  
WO/2020/020578A1
Turbomachine (100) having a turbo housing (56) and an impeller (1) which is mounted such that it can be moved about a rotational axis (30), which impeller (1) defines an inflow region (8) and an outflow region (9) of a working medium on ...  
WO/2020/021199A1
The invention relates to a turbomachine blade having a turbine blade airfoil (12) extending in a first direction between a leading edge (18) and a trailing edge and in a second direction, which is substantially perpendicular to the first...  
WO/2020/018090A1
The present invention relates to a turbine nozzle (18) that includes a first body (102) of a metal material (104) and a second body (106) of a ceramic matrix composite material (108). A gap (110) is disposed between the first body (102) ...  
WO/2019/066750A3
Instead of cooling the turbine disk blades of the gas turbine engines using a very stressful and expensive method of stealing from the compressor air at a temperature of 650 degrees Celsius, it is possible to provide a much effective coo...  
WO/2020/013863A1
An airfoil (10) for a turbine engine includes an array of pins (30) positioned in an internal cavity (26) of the airfoil (10), such that cooling channels (52, 54) are defined in the interspaces between adjacent pins (30). Each pin (30) e...  
WO/2020/011837A1
Described are a guide vane for a variable turbine geometry and a turbine assembly provided with same. The guide vane is characterised in that it has an outer face that is at least partly concave in design. The inner face on the opposite ...  
WO/2020/011673A1
The invention relates to a method for coating a part comprising a surface that has cooling fluid openings that adjoin cooling fluid ducts inside the part. The invention further relates to a device for analyzing the surface of a part comp...  
WO/2020/007915A1
The present disclosure relates to a method of manufacturing an aerofoil structure for a gas turbine engine, wherein the aerofoil structure comprises a root (202) configured to be received in a rotor disc (240) of the gas turbine engine, ...  
WO/2020/008142A1
The invention relates to a device (10) for attaching a wear strip to at least one contact face of a turbo engine rotor blade, which device comprises heat-generating means (36) for activating a product for attaching the wear strip to the ...  
WO/2020/007916A1
There is disclosed a method of manufacturing a composite component. A preform (140) for the component is laid - up on a lay - up tool (130) so that a first surface of the preform conforms to a lay - up profile (136) of the tool. The pref...  
WO/2019/202259A3
Turbine (1) for a turbomachine, comprising a casing (4) and a turbine nozzle diaphragm stage (2), the nozzle diaphragm stage (2) of the turbine (1) comprising an outer metallic ferrule (9) firmly joined to the casing (4), an inner metall...  
WO/2020/001849A1
The invention relates to a method for the additive manufacturing of a structure (10, 10'), in particular by a powder bed method. The method comprises, layer by layer, a) applying a layer (S) of a base material (P), in particular a pulver...  
WO/2019/245546A1
A cooled turbine blade assembly is provided. The cooled turbine blade assembly includes a hollow turbine blade airfoil extending span-wise radially outward from a platform. The turbine blade airfoil includes a leading edge and a trailing...  

Matches 301 - 350 out of 23,809