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Matches 1 - 50 out of 22,269

Document Document Title
WO/2018/189432A1
The invention relates to a turbine blade comprising a blade root and a blade (13) extending radially outwards from the blade root (12), said blade (13) comprising a first inner cooling circuit comprising a lower surface cavity (33, 36) e...  
WO/2018/189380A1
A component (1) for a turbomachine, which is provided with a protective coating (24) at least in a subregion (22) of its surface (20), is intended to be comparatively easy and thus cost-effective to produce and yet exhibit a particularly...  
WO/2018/189434A2
The invention relates to an aviation turbine blade (10), characterised in that it comprises at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second throu...  
WO/2018/190932A2
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...  
WO/2018/189433A2
The invention relates to an aviation turbine blade (10) extending radially from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling cir...  
WO/2018/186921A2
A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have...  
WO/2018/184788A1
The invention relates to a method for sealing an annular gap (11) in a turbine with a housing (1) and a rotor (2), which is arranged in the housing (1), is mounted to rotate about its central longitudinal axis, and is equipped with a plu...  
WO/2018/186891A1
A cooling assembly comprises a cooling cavity disposed inside of a turbine assembly. The cooling cavity is configured to direct cooling air inside a body of the turbine assembly. The cooling assembly comprises a cross-bank fluidly couple...  
WO/2018/185445A1
The invention relates to a diffuser (5) of a radial or hybrid compressor (2) comprising an internal shroud (20), an external shroud (30) and a series of vanes (10), the trailing edge (12) of each vane (10) being curved in such a way that...  
WO/2018/184782A1
The use of MAX phases creates a large aluminum or chromium reservoir for forming oxidation-inhibiting layers.  
WO/2018/180781A1
Provided is a gas turbine (A) using a denitration catalyst and ammonia as a reducing agent for the denitration of combustion gas, wherein the ammonia is supplied, along with cooling air supplied from a compressor (1), to turbine vanes (3...  
WO/2018/182816A1
A cooling circuit for a trailing edge region of a turbine airfoil where the trailing edge is relatively thin, the cooling circuit having a series of aftward-flowing channels alternating with a series of forward-flowing cooling channels, ...  
WO/2018/177864A1
The invention relates to a turbocharger (1) for an internal combustion engine, comprising - a bearing housing (41), in which a rotor shaft (14) is mounted rotatably about a rotor axis of rotation (15); - an exhaust gas turbine (20) havin...  
WO/2018/181559A1
The present invention addresses the problem of providing a thermal barrier coating film (13) which exhibits high durability even in a gas turbine used in a molten salt environment such as a heavy oil fired gas turbine, and which can be f...  
WO/2018/178603A1
The invention concerns a turbine component, such as a turbine blade or a distributor fin, for example, comprising a substrate made from single-crystal nickel superalloy, and a metal sublayer covering the substrate, characterised in that ...  
WO/2018/175003A1
A system is disclosed including a first blade (102), a second blade (104), and a snubber (100) disposed between a pressure side (106) of the first blade (102) and a suction side (108) of the second blade (104). An inclination angle of a ...  
WO/2018/175356A1
The invention is related to a bladed rotor system (10) for a turbomachine including blades (14) mounted circumferentially on a rotor disc (12), and a plurality of under-platform dampers (30). Each damper (30) is located between adjacent ...  
WO/2018/167384A1
The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising: - a step of producing a blank from at least two parts (50, 51), at least one of which is...  
WO/2018/169668A1
A bladed rotor system (10) for a turbomachine includes a row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) with a mid-span snubber (30). The row of blades (14) includes first (H) and second (L) set...  
WO/2018/169665A1
A bladed rotor system (10) includes a circumferential row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) and a shroud (30) attached to the airfoil (16) at a span-wise height of the airfoil (16). The...  
WO/2018/167632A1
The present invention relates to a method for constructing bladed rings for radial turbomachines. The method comprises: preparing a cylindrical block (M; M1, M2); making in the cylindrical block (M; M1, M2) a wavy circumferential cut (28...  
WO/2018/164149A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/164693A1
Processes are described herein which 3D print a ceramic fiber composite (24, 48) in a printed pattern (308) on a ceramic matrix composite (CMC) component (300) in order to define a plurality of channels (312) between adjacently deposited...  
WO/2018/162485A1
A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turb...  
WO/2018/164791A1
A rotor assembly is provided. The rotor assembly includes a plurality of blades spaced circumferentially. An airfoil of each blade includes a pressure side, a suction side, a pressure side nub extending from the pressure side, and a suct...  
WO/2018/163877A1
A first turbulator 41R which is at least one of a plurality of turbulators comprises: a first section 411 which has a constant projection height from an inner surface 40S; and a second section 412 which is connected at one end to the fir...  
WO/2018/164598A1
The present invention provides a supply system (7) for gas turbine component cooling, wherein the gas turbine component is a hollow component (1) that is required to be cooled, for example a gas turbine blade, a gas turbine vane, a gas t...  
WO/2018/164150A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/162695A2
The invention relates to a fastener for rotating blades (1) which is suitable for steam turbines, gas turbines or compressors, the base geometry being optimally configured.  
WO/2018/164148A1
This cooling structure for a turbine blade (1) is provided with a lattice structure (23) formed by a first rib pair (33A) and a second rib pair (33B) which are disposed in a cooling passage (17) and overlap each other in a lattice shape,...  
WO/2018/157958A1
The invention relates to a turbine stage, comprising at least one turbine rotor (1) and a plurality of turbine blades (2) arranged over the circumference of the turbine rotor (1), and comprising at least one coupling element (3), bores (...  
WO/2018/158544A1
The invention relates to a blade (100) comprising: a vane body (110) made of composite material having a fibrous reinforcement (120) exhibiting a three-dimensional weave and densified by a matrix, the reinforcement comprising a first par...  
WO/2018/158522A1
A fibrous preform for a turbomachine vane, comprising a main fibrous structure (40) obtained by one-piece three-dimensional weaving, said first main structure (40) comprising a first longitudinal section (41), suitable for forming a vane...  
WO/2018/159686A1
In a rotating machine (1) a tip shroud (51A) of a moving blade (50) includes: a plurality of shroud outer peripheral surfaces (53A, 53B, 53C) provided in such a way that the radial direction positions thereof are positioned further towar...  
WO/2018/154724A1
Provided is a method for measuring a pre-twist amount of a blade, the method including: a spreading dimension acquiring step; a misalignment acquiring step; a correcting step; and a pre-twist amount acquiring step. In the spreading dimen...  
WO/2018/156270A1
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/2018/155640A1
An axial flow rotating machine (100) comprises a rotating shaft (1), a rotor blade (4), a casing (2), and a stator blade (7). A stator blade body (70A) comprises: a stator blade first shape part (73A) in which a stator blade intermediate...  
WO/2018/156256A1
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/2018/153796A1
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...  

Matches 1 - 50 out of 22,269