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Matches 51 - 100 out of 22,269

Document Document Title
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/2018/132161A3
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/2018/132629A1
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...  
WO/2018/132084A1
The invention relates to a rotor (1) for a turbomachine (2) having an annular flow path (3) as seen in cross section, com-prising at least two shaft collars (5, 6) that are arranged axially adjacently and at a predetermined spacing, form...  
WO/2018/128609A1
A turbine rotating component (18) includes an airfoil (20) extending radially from a platform (40). An axial end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12). Th...  
WO/2018/127664A1
The invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface and compr...  
WO/2018/129438A1
Various arrangements of a turbine for a rotating coalescer element of a crankcase ventilation system for an internal combustion engine are described. In some arrangements, the turbine is an impulse turbine, which is also known as a pelto...  
WO/2018/127652A1
The present invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface a...  
WO/2018/123045A1
A scroll part of a turbine housing is configured such that a concave distribution is included in at least part of a first graph of which the horizontal axis is an angular position θ in the circumferential direction of the scroll part an...  
WO/2018/115763A1
A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by the intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (2...  
WO/2018/116333A1
A turbine rotor blade assembly characterized in that in the two-dimensional coordinates shown in fig. 5, A, CF, T, and L given below are set so as to satisfy 1.2 × 105 ≤ (A × CF)/(T × L) ≤ 17 × 105. Formula (1): (A × CF)/(T × L...  
WO/2018/114766A1
The invention relates to a method for joining hot gas component segments (6, 7), comprising the following steps: providing the segments (6, 7) to be joined; applying complementary joining elements (8) to the surface of the segments (6, 7...  
WO/2018/119391A1
A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back w...  
WO/2018/114659A1
A method for producing a wind turbine rotor blade (200) is disclosed. The wind turbine rotor blade (200) has at least one inner blade section (210) and an outer blade section (220) as well as a connection element (600). The inner blade s...  

Matches 51 - 100 out of 22,269