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Matches 351 - 400 out of 22,991

Document Document Title
WO/2018/153796A1
A turbomachine component having an aerofoil, such as a blade or a vane, is presented. The turbomachine component includes an aerofoil cavity bordered by a suction side wall and a pressure side wall. A cooling channel, for flow of cooling...  
WO/2018/156408A1
Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the l...  
WO/2018/155652A1
In an axial flow rotary machine according to the present invention, a structure comprises a casing-side fin (42). An upstream-side inclined surface (45) that is inclined from the upstream side toward the downstream side is provided to a ...  
WO/2018/156255A1
Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the l...  
WO/2018/156265A1
A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the...  
WO/2018/153558A1
A component (50) comprising a nickel based alloy substrate (102) having a coating system (100) comprising a CrAl layer (104) overlaying the nickel based alloy substrate (102), a NiCrAlY layer (106) overlaying the CrAl layer (104) and a y...  
WO/2018/155532A1
A supercharger provided with: a turbine housing which includes a hub-side scroll flow channel and a shroud-side scroll flow channel; and a turbine rotor which includes a leading edge for receiving operating fluid from the hub-side scroll...  
WO/2018/156235A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial center...  
WO/2018/156406A1
Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the l...  
WO/2018/153529A1
What is described is a rotor blade module (11) for securing to a rotor part in order to form a rotor blade ring in a steam turbine. The rotor blade module (11) has (a) a root plate (13), (b) a blade airfoil (12) that extends from one sid...  
WO/2018/156407A1
Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the l...  
WO/2018/155635A1
A turbine moving blade comprises a diametrically extending blade body (50) in which a negative pressure surface (51) that faces one way in a circumferential direction and a pressure surface (52) that faces the other way in the circumfere...  
WO/2018/153446A1
A turbine impeller (1) for a turbomachine, in particular for an exhaust gas turbocharger, wherein the turbine impeller (1) comprises: a hub (4), a first end (2) and a second end (3), wherein an outer contour (4a) of the hub (4) narrows f...  
WO/2018/155636A1
In an axial flow rotary machine according to the present invention, a moving blade (4) comprises a moving blade shroud (41) and a shroud-side fin (44), and a small gap is formed between said shroud-side fin (44) and a casing (2). The cas...  
WO/2018/152391A1
At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. Th...  
WO/2018/151609A1
Fan, turbine or pump with a substantially helically shaped blade, wherein the fluid intake is axially aligned to a longitudinal axis. The blade within the fluid intake portion has a flat and/or concave pressure face, and a root that is h...  
WO/2018/151251A1
A steam turbine is provided with: a rotating shaft (1); a moving blade (4) including a platform (43) and a moving blade main body (40); a casing (2); a stationary blade (7) including a stationary blade main body (70) and a stationary bla...  
WO/2018/149569A1
The invention relates to a rotor part (RPT) of a rotor (RTR), in particular an impeller (IMP) of a radial-flow turbomachine (RTM), comprising a flow-guiding surface, which is to be wetted and is at least 97% closed as a proportion of sur...  
WO/2018/152328A1
Thermal spray powder including a metal and/or ceramic powder composition and porosity forming fibers and/or fiber agglomerates mixed within or with the powder composition. An exemplary TBC or abradable thermal spray coating can be made b...  
WO/2018/145900A1
The invention relates to a slip, a prepreg, a laminate, a green ceramic and a ceramic matrix composite turbine component produced therefrom. The invention provides for the first time a glycerin-containing slip for producing a CMC compone...  
WO/2018/147162A1
A blade (12) of an axial flow machine is provided with: an airfoil part (13) having a dorsal surface (13a) and a ventral surface (13b); an end wall serving as a shroud (15) or a platform (14); and a fillet (16) provided along a connectin...  
WO/2018/146046A1
The invention relates to a method for modifying a turbine (1) with rotor blade rings (3a, 3b, 3c, 3d) and guide vane rings (4a, 4b, 4c, 4d) arranged in a conical housing (2), in which an original rotor blade ring (3a, 3b, 3c, 3d) at a fi...  
WO/2018/146403A1
The invention relates to a blade of a high-pressure turbo-engine turbine, comprising: • - a blade airfoil (13) extending in a span direction (EV), terminating in an apex (S) and comprising a lower surface (16) and an upper surface (17)...  
WO/2018/147875A1
There is provided a component (10) having a plurality of laminates (12) formed from a ceramic matrix composite material stacked on one another to form a stacked laminate structure (14). A seal (28) formed from a resolidifiable ductile an...  
WO/2018/146862A1
Provided is a fan blade which is made of a composite material and which will not suffer damage even if a large foreign object collides with the fan blade. A fan blade (20) is provided with a blade body (21) composed of a composite materi...  
WO/2018/144658A1
This application provides controlled flow runners (130) for use with steam turbines. Example controlled flow runners (130) may include a tip, a blade (132) adjacent to the tip, the blade (132) having a top width (134), a middle width (13...  
WO/2018/143997A1
A turbine blade (10) for a gas turbine rotor, comprising successively along a radial direction of said gas turbine, a blade root for attaching the turbine blade (10) to a turbine rotor, a platform (12), an aerodynamically shaped hollow a...  
WO/2018/141504A1
The invention relates to a turbine blade (10) or turbine vane (20) for a gas turbine, comprising successively along a radial direction of said gas turbine, a root (12) for attaching the turbine blade (10) or turbine vane (20) to a carrie...  
WO/2018/141574A1
The invention relates to a non-metal turbine component, particularly a gas turbine component, for example for stationary gas turbines, consisting of ceramic matrix composite (CMC) materials. A CMC turbine component comprising fine and co...  
WO/2018/144134A1
A method of repairing a blisk having a hub with circumferentially spaced blades. The method can include removing a portion of a blade and replacing the portion with a replacement piece. The method can further include welding the replacem...  
WO/2018/141739A1
A wall (12) of a hot gas part comprises: ∙ a first surface (14) subjectable to a cooling fluid (17); ∙ a second surface (16) located opposite of the first surface and subjectable to a hot gas (15); and ∙ one film cooling hole (18) ...  
WO/2018/142370A1
The present invention pertains to a layered structure intended to be used for protecting wind turbine blades against lead ing edge erosion. The layered structure is capable to resist the impact energy of incoming particles and/or rain dr...  
WO/2018/138445A1
The invention relates to a method for removing at least one portion of a metal part (3) bonded to a part made of composite material (2) of the carbon-epoxy type, comprising a step of degrading the bonding interface between the metal part...  
WO/2018/140139A1
The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame...  
WO/2018/138155A1
The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more...  
WO/2018/140111A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a dow...  
WO/2018/138296A1
The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includ...  
WO/2018/138438A1
The invention relates to a wheel blade (40) for a turbomachine compressor. The blade (40) comprises a body (41) extending between the root (P) of the blade in the direction of the height (Y-Y) of the blade. The body (41) extends from a l...  
WO/2018/138439A1
The invention relates to a vane configured to be placed with a plurality of identical vanes so as to form an impeller of an aeronautical engine, the impeller defining an axis, the vane including a blade (10) having a leading edge (10a) a...  
WO/2018/135283A1
In the present invention, a structure for cooling a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a...  
WO/2018/135212A1
This steam turbine (10) is provided with: a rotor (12); a casing (20) for rotatably housing the rotor (12); and a first stage (40) including a first-stage stator blade (42) fixed to an inner wall part (22) of the casing (20) and a first-...  
WO/2018/134093A1
The invention relates to a method for producing a cavity (4) in a blade platform (3) of a blade (1), in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bor...  
WO/2018/136182A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a dow...  
WO/2018/136042A1
A turbine element for high pressure drop and heat transfer. The turbine element includes a plurality of elements (16) radially placed in columns together aligned in a series of rows of at least four rows across an interior surface of an ...  
WO/2018/136162A1
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the ...  
WO/2018/132629A1
A method is provided for machining an airfoil section (12) of a turbine blade or vane produced by a casting process. The airfoil section (12) has an outer wall (18) delimiting an airfoil interior having one or more internal cooling passa...  
WO/2018/132123A1
The invention is related to a stator vane assembly for a gas turbine engine in which both higher pressure cooling air and lower pressure cooling air are both supplied to the stator vane assembly to cool both an airfoil (20) and inner and...  
WO/2018/130615A1
The invention relates to a process of obtainment of a dense hydrophobic icephobic wear- resistant coating by means of Cold Gas Spray technique, to the coatings obtained by said process, its use as coating in wind turbine blades, to a win...  
WO/2018/132161A2
A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket de...  
WO/2018/131213A1
This radial-inflow-type turbine comprises: a turbine wheel including a rotor blade wherein a hub-side end of a front edge is located more toward an inner side, in the radial direction, than a shroud-side end of the front edge; and a hous...  

Matches 351 - 400 out of 22,991