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Matches 401 - 450 out of 23,744

Document Document Title
WO/2019/187819A1
Provided is a blade manufacturing method by which a blade of a stable quality can be manufactured. The present invention involves: a shaping process in which a blade is molded by means of metal injection molding by injecting metal powder...  
WO/2019/188780A1
This turbine blade comprises a platform, a blade-shaped part having a pressure surface and a negative-pressure surface that extend in a blade-height direction from the platform and that also extend between a leading edge and a trailing e...  
WO/2019/186144A1
The invention relates to an axial turbine with a rotating outer casing (4) and stationary shaft (8) and a method for manufacturing a rotor section (10) for that turbine. The turbine comprises an axially arranged series of rotor sections ...  
WO/2019/185246A1
The invention relates to a moulded part made oxide composite fibre ceramic, referred to below as a "CMC moulded part", such as can be used, for example, in a turbine component, in a burner and/or in an exhaust gas system, in particular o...  
WO/2019/189355A1
A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed be...  
WO/2019/187435A1
This gas turbine for an aircraft comprises: a moving blade (24) having a moving blade body (41) extending diametrally outward from a rotor that rotates about an axis, and a fin (43) protruding from an outer peripheral surface (42a) of a ...  
WO/2019/188588A1
This turbine rotor blade is provided with a blade body including a belly-side blade wall and a back-side blade wall. The blade body includes; a serpentine flow passage comprising a cooling flow passage divided into a plurality of portion...  
WO/2019/185914A1
A fixture (1) for use in a coating operation, preferably in the shape of a carousel rotatable around a central axis (L), comprising a support structure (5) to which a shield is fixed, the shield has a number of retainer openings (19), ea...  
WO/2019/185394A1
The invention relates to a CMC moulded part, in particular a CMC moulded part having means for fastening and/or for installation, in particular for fastening in a curved, bent or cylindrical surroundings and a method for production there...  
WO/2019/190539A1
A turbine stage (100) includes a first and a second airfoil (10a, 10b) extending respectively from a first and a second platform (12a, 12b) that form an endwall (40) for a flow passage. The endwall (40) has a nominal surface (60) that is...  
WO/2019/186046A1
The invention principally relates to a stator vane (1) of a turbine of a gas turbine engine, comprising an outer platform (5) and an inner platform between which there extends an outer wall (7) forming an outer skin, characterized in tha...  
WO/2019/190540A1
A turbine stage (100) includes an array of airfoils (10) spaced apart circumferentially to define a flow passage (50) therebetween for channeling a working medium. The airfoils (10) extend radially outward from an inner endwall (20) loca...  
WO/2019/186029A1
A method for manufacturing a vane from a composite material with a fitted metal leading edge comprises: - successively applying, on a template (211) of the leading edge of the vane to be manufactured, a first layer of a base material (20...  
WO/2019/186170A1
A turbine wheel comprises a shroud component (10) and a bladed disc component (20). The shroud component comprises a shroud structure(ll), a hub structure (12) and at least one spoke (13a- f) formed integrally therewith and extending bet...  
WO/2019/185526A1
The invention relates to a turbine blade (10) for a gas turbine having a blade leaf (16) comprising a front edge (18) around which a hot gas (S) can flow, from which a suction side wall (22) and a pressure side wall (24) extend to a rear...  
WO/2019/179722A1
A ceramic material is provided by deliberately choosing the additions of oxides to form zirconium oxide, in particular for the use of a layer system which has a high resistance to sintering, high expansion tolerance and low thermal condu...  
WO/2019/180382A1
The invention relates to a turbomachine stator vane formed of a hollow blade (32) with a leading edge (32A), a trailing edge (32B), a pressure-face wall (32C) and a suction-face wall (32D) extending between a vane root and a vane tip, an...  
WO/2019/180366A1
The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23)...  
WO/2019/183269A1
Systems, computer-implemented methods and/or computer program products that facilitate aviation engine inspection are provided. In one embodiment, a computer-implemented method comprises: generating, by a system operatively coupled to a ...  
WO/2019/179583A1
A device for remedying erosion problems on a wind turbine blade (1). The device is characterized in that it comprises a shock-absorbing and erosion-resistant and UV -resistant profile (4) for positioning on the front edge of a wind turbi...  
WO/2019/179702A1
The invention relates to a method for producing cooling channels in ceramic fibre-reinforced matrix material CMC shaped bodies and to a ceramic fibre-reinforced matrix material CMC shaped body with cooling channels and produced according...  
WO/2019/179843A1
The invention relates to a turbomachine with an impeller (1) which is mounted in a rotatable manner about a rotational axis (A) and which defines an inflow region (2) and an outflow region (3) on the front face and interacts with a housi...  
WO/2019/177607A1
A method of additively manufacturing or repairing a superalloy component utilizing at least a double solution heat treatment and sub-cooling is presented. The at least double solution heat treatment includes heating the tip of a superall...  
WO/2019/177600A1
A cooling assembly comprises a coolant source chamber inside an airfoil that directs coolant inside the airfoil that extends between a hub end and a tip end that includes a tip body and tip rail along a radial length. A first body coolin...  
WO/2019/178476A1
A method for manufacturing a rotor blade root assembly includes placing outer skin layer(s) onto a blade mold and arranging a root plate with a plurality of through holes adjacent to an end face of the blade mold. The method also include...  
WO/2019/174836A1
A ceramic material which contains yttrium oxide as the stabilizer and at least one of the materials erbium oxide or ytterbium oxide provides a phase having sintering stability for a ceramic material for ceramic layers and a ceramic layer...  
WO/2019/177598A1
A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end i...  
WO/2019/177599A1
A turbine engine (32) includes at least one blade (10) that includes an airfoil (12) extending span-wise along a radial direction (Ra). The turbine engine includes a shroud (26) positioned along a tip end (22) of the airfoil (12) extendi...  
WO/2019/086848A3
A material for water droplet erosion- and corrosion-resistant coatings, comprising metallic tungsten alloyed with carbon in a substantially uniform nano-structure that is substantially free of oxygen, other than at surface portions expos...  
WO/2019/171265A1
A process for the production of a monolithic metal component for turbine engines, by means of a technique of the "additive manufacturing" type, is described. The component has a substantially cylindrical shape and is obtained in a laser ...  
WO/2019/172020A1
Provided are: a leading edge cover member suitable for use, as a countermeasure against water droplet erosion, for example, in a composite-material blade body used in an industrial gas turbine compressor; a leading edge cover member unit...  
WO/2019/166244A1
A component comprising at least two different iron-based compositions in different regions of the component, including a first iron-based composition comprising 11.0-15.0 wt% chromium; 1.0-4.0 wt% nickel; 5.0-8.0 wt% cobalt; and iron. Th...  
WO/2019/168590A1
A gas turbine engine includes a first passage 19 formed by an exterior wall 18 of a combustor and an inner wall 17 within the gas turbine engine and a second passage 20 formed by the inner wall 17 and a rotating arm 16. A pre-swirl cavit...  
WO/2019/168501A1
A gas turbine engine includes a pre-swirl cavity. There is a first passage and a second passage within the gas turbine engine. The gas turbine engine has a first self-adjusting seal disposed within the pre-swirl cavity and a second self-...  
WO/2019/166228A1
The invention relates to a fiber composite material (1), comprising ceramic fibers (2) and a ceramic matrix (3), in which the fibers (2) are embedded, wherein a respective sliding layer (4) is arranged between the respective fibers (2) a...  
WO/2018/164149A8
This cooling structure for a turbine airfoil (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...  
WO/2019/168174A1
A thermal barrier coating which comprises a metal bonding layer that is formed of an alloy containing Al, a thermal barrier layer, and an intermediate layer that is arranged between the metal bonding layer and the thermal barrier layer. ...  
WO/2018/164150A8
This cooling structure for a turbine airfoil (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...  
WO/2018/164148A8
This cooling structure for a turbine airfoil (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 shap...  
WO/2019/162464A1
The invention relates to a method of machining a bore (803) extending from an outer wall of a workpiece (800), preferably a turbine blade (800), to an internal cavity (814) of the workpiece (800) with a liquid-jet guided laser (802). A b...  
WO/2019/161959A1
The invention relates to a component (1) comprising at least one internal filler body (2) and an outer body (3) that at least partially surrounds said internal filler body (2). The outer body (3) is produced using an additive manufacturi...  
WO/2019/160564A1
A rotor having at least two vanes includes a plurality of elongated arched support ribs rigidly connecting at axially spaced intervals to a shaft of the turbine. The arched support ribs are disposed transverse to the shaft and provide a ...  
WO/2019/158144A1
The invention relates to a tool for maintaining engines, having a multi-channel supply line (30) that has at least one electrical power supply and/or data line channel (31) and at least one gas, liquid and/or material channel (32). In th...  
WO/2019/160547A1
An assembly of turbine blades (10) or vanes includes a first (12a) and a second (12b) airfoil extending span-wise from a first (14a) and a second (14b) platform respectively. The first (14a) and the second (14b) platform respectively hav...  
WO/2019/154734A1
The invention relates to a rotor vane (10) for an aircraft turbine engine, said vane having an axis (A) of rotation once it has been rigidly connected to a rotor and a stacking axis (X). The vane comprises a blade (16) extending between ...  
WO/2019/156724A1
Toroidal propeller. The propeller includes a hub supporting a plurality of elongate propeller elements in which a tip of a leading propeller element curves into contact with a trailing propeller element to form a closed structure with in...  
WO/2019/149857A1
The invention relates to a particle powder, a number higher than 95% of the particles having a circularity greater than or equal to 0.85, the powder containing more than 98% of a stabilised oxide which is selected from stabilised zirconi...  
WO/2019/149856A1
The invention concerns a powder of particles, more than 95% by number of said particles having a circularity greater than or equal to 0.85, said powder containing more than 88%, preferably more than 90%, of a silicate of one or more elem...  
WO/2019/150042A1
The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring ...  
WO/2019/149850A1
The invention relates to a feed powder for the production, by thermal spraying, of a dense and vertically cracked thermal barrier coating, said powder - consisting of, for more than 95% by weight, molten feed particles each consisting, f...  

Matches 401 - 450 out of 23,744