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Matches 1 - 50 out of 8,637

Document Document Title
WO/2017/176186A1
The present invention relates to a turbine arrangement driven by exhaust gases from a combustion engine (2). The turbine arrangement comprises a turbine housing (7), a turbine wheel (6) rotatably arranged in the turbine housing (7), a fi...  
WO/2017/169537A1
A dehydrogenation processing method for turbine blades in a steam turbine, said method having a step in which heating steam is supplied to the steam turbine casing when a steam turbine plant is started up or is stopped, thereby heating t...  
WO/2017/168647A1
Provided is a fixed vane turbo charger, comprising: a housing including an impeller, an impeller housing space that houses the impeller, a scroll flow passage that is formed on the outer peripheral side of the impeller, and a communicati...  
WO/2017/164884A1
A gas turbine engine has an outer ring (15) formed by integrated exit pieces (10) and surrounds an inner ring (16). A seal section (20) having an L-shaped cross-section is positioned in a respective slot (11, 12) in the outer and inner r...  
WO/2017/164258A1
A structure for supporting turbine nozzles (13) and shrouds (21) opposing rotor blades adjacent to the nozzles by means of a turbine casing (23) covering a turbine (5) in a gas turbine. The front and back end parts of a circumferential f...  
WO/2017/158637A1
A turbine equipped with a cylindrical casing and turbine stator blades arranged along the circumferential direction in the interior of the casing, said turbine blades having: a blade effective section; a cooling medium flow path for circ...  
WO/2017/158264A1
The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, involving manufacturing at least one turbine shroud segment (26), placing the turbine shroud segment (26) in a lower mold in such a way that an...  
WO/2017/158037A1
The repair member (200) comprises an inner platform portion (201) designed to replace part of the inner platform of a damaged vane, an outer platform portion (202) designed to replace part of the outer platform of a damaged vane, and an ...  
WO/2017/158266A1
The invention relates to a stator ring (20) of a flow path, preferably secondary, of a turbomachine (1), said ring (20) comprising: – an inner platform (52, 56) and an outer platform (54), – a plurality of stators (40) extending radi...  
WO/2017/155914A1
A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-ac...  
WO/2017/154785A1
A flow path forming plate has formed therein a gas path surface (64p) in contact with combustion gas, an end surface formed at the peripheral edge of the gas path surface (64p), a first side through channel (90i), and a plurality of end ...  
WO/2017/154257A1
Tapered surface sections 21f, 22f are formed on inner-side surfaces of base sections 21a, 22a facing a flow path 14 at an outer band part 21 and an inner band part 22 of one of turbine stator blades 11, said turbine stator blades 11 bein...  
WO/2017/151146A1
An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which fl...  
WO/2017/149414A1
The present invention relates to a method of manufacturing a bladed ring (9) for radial turbomachines, comprising the steps of : assembling a first support ring (15) with a second support ring (22), with a plurality of blades (27), with ...  
WO/2017/145623A1
An insert assembly (79) equipped with an insert (80), a reinforcing member (85), and a holding member (90). The insert (80) is affixed to one end of a blade main body (51) in the radial direction. The reinforcing member (85) is arranged ...  
WO/2017/144805A1
The invention relates to a rectifier (1) for an aircraft turbomachine compressor, the rectifier comprising an inner ferrule (24), an outer ferrule (26), and stator blades (28) secured to the inner and outer ferrules, the rectifier also c...  
WO/2017/145190A1
A steam turbine 90 according to the present invention is provided with: stator vanes 10 provided in a compartment 92 inside a casing through which steam flows from an upstream side toward a downstream side; and support means for supporti...  
WO/2017/140985A1
The invention relates to a turbine shroud sector (10) made of ceramic matrix composite material having a portion forming an annular base (12) with an inner surface intended for defining the inner surface of a turbine ring (1) when the sh...  
WO/2017/140986A1
The present invention relates to a method for manufacturing a part made of a ceramic matrix composite material, the method including at least the following step: infiltrating a fibrous preform with a molten composition including mostly s...  
WO/2017/134976A1
A method for implementing an abradable coating comprising: a pattern-forming step S1 in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a f...  
WO/2017/129342A1
The invention relates to a continuous flow machine (2) having a rotor (4) that is mounted such that it can rotate about a rotational axis (6), and a diffuser (24) having a plurality of diffuser blades (28). So that the continuous flow ma...  
WO/2017/131650A1
A gas turbine engine has a transition duct assembly. Between two adjacent transition ducts (20) there is a transition side groove (23) that is formed by transition side rails (22). In this transition side groove (23) is inserted a side s...  
WO/2017/130144A1
The invention relates to equipment for implementing a method for depositing a vapor-phase metal coating onto turbine engine parts such as, for example, blades (14). Said equipment comprises at least one basket (2) defining a chamber (9),...  
WO/2017/127043A1
Turbine section (26) vane ring (44, 46) swallowing capacity, or throat cross section is selectively varied, through use of bi-cast vanes (50). The bi-cast vanes share a common, prefabricated vane airfoil profile (52), as well as subseque...  
WO/2017/127255A1
A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straigh...  
WO/2017/125289A1
An aerofoil (100) for a gas turbine (10) comprises: - an external surface (128) extending along a first axial direction between a leading edge (133) and a trailing edge (135) and extending along a second radial direction between a base (...  
WO/2017/126038A1
A stationary stator vane-type rotary machine is provided with: a rotating shaft; an impeller; an impeller housing having therein a scroll passage formed on the outer peripheral side of the impeller; a bearing housing connected to the imp...  
WO/2017/122632A1
A blade pull-out device for pulling a blade out in a circumferential direction of a blade ring along a groove, the blade having been engaged in the groove which extends in the circumferential direction in the inner peripheral side of the...  
WO/2017/115642A1
Before subjecting a turbine rotor blade to a heat treatment for removing residual stress, an adhesion cleaning step (scale cleaning step) is executed, wherein an ultrasonic cleaning process (steps S22, S25), in which the turbine rotor bl...  
WO/2017/108661A1
The invention relates to a turbine blade (10) for a thermal turbomachine, having a blade airfoil (20) around which a hot gas can be made to flow and which comprises a suction-side and a pressure-side side wall (22, 24). The blade airfoil...  
WO/2017/109438A1
The invention relates to a turbine nozzle (D) for a turbomachine comprising a plurality of vanes (A1-A3) distributed circumferentially and defining between each other fluid guiding and acceleration channels (A, B, C), at least three chan...  
WO/2017/110322A1
Vapor turbines (120, 130, 140) are provided with: a cooling vapor passage (69Ba) which passes through a casing (62 (outer casing 62A and inner casing 62B)) along a superheated vapor supply pipe (69A) to reach a gap (65B); and a cooling v...  
WO/2017/105405A1
A gas engine turbine has a transition duct (100) that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel (130) is formed through the transition duct panel (112), the exi...  
WO/2017/105260A1
A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathwa...  
WO/2017/103411A3
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material, forming a turbine ring (1), and a ring support structure (3) having first and second annular flanges (32, 36), each ring sect...  
WO/2017/105380A1
An airfoil (30) for a turbine (10), wherein the airfoil (30) includes leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The airfoil (30) includes a core support structure (34) having first (46) and second...  
WO/2017/103411A2
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material, forming a turbine ring (1), and a ring support structure (3) having first and second annular flanges (32, 36), each ring sect...  
WO/2017/094292A1
A sliding component (10) provided with a wear-resistant coating comprises: a sliding component (12); and a wear-resistant coating (14) provided on a sliding surface (12a) of the sliding component (12) and formed of a cobalt alloy that co...  
WO/2017/095358A1
An improved interface (111) between a combustion basket ring and a transition assembly (113) in a can-annular gas turbine engine. Traditionally, a spring clip is positioned within a circumferential gap between a combustion basket ring an...  
WO/2017/093461A1
The present invention relates to a component (100) for a fluid flow engine, such as a gas turbine (100), comprising a first side (1), e.g. a top side and a second side (2), e.g. a bottom side, wherein the component (100) further comprise...  
WO/2017/090502A1
A flow path forming plate (60i) is provided with a plate body (61i), a peripheral wall (65i), and a shelf (71). The plate body (61i) includes: a gas-path surface (64p) facing a gas flow path side; and an inner surface (64i) facing a side...  
WO/2017/091666A1
An air flow assembly, such as a fan assembly, and associated methods are shown that may include one or more media dispensing nozzles. Examples of assemblies and methods are shown that include nozzles located within hollow vanes. Other ex...  
WO/2017/088008A1
The present invention provides an energy conversion turbine having at least the following components: a central shaft having a rotational axis, a series of blades in mechanical connection with and disposed around the central shaft, where...  
WO/2017/085380A1
The invention relates to a blade of a turbomachine guide vanes assembly, which blade is equipped with a cooling system comprising an insert (22) arranged inside an internal cavity (24) of the said blade, connected to an inlet (26) for bl...  
WO/2017/080826A1
The invention relates to a gas turbine having a compressor, a mid-section and a turbine, wherein a diffusor (11) is arranged at the end of the compressor. This diffusor (11) comprises a diffusor housing section (12) partially surrounding...  
WO/2017/082876A1
A gas engine turbine has a trailing edge duct (110) that is used for the transition duct. The trailing edge duct (110) has an extension flange (115) located at its outlet (117). The extension flange (115) has a contoured receiving sectio...  
WO/2017/078122A1
In a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade according to the present invention, a blade body (51) having hollow shape, cavities (52, 53, 54) provided in...  
WO/2017/069145A1
In the present invention the end plate (60) of a blade (50) has a gas path surface (61) facing a combustion gas flow passage (49) side, an end surface (63) along the edge of the gas path surface (61), multiple passages (81p), and a baseb...  
WO/2017/063786A1
The present invention relates to a method of manufacture of a channelling tube (10). The tube is realised by rolling a metal sheet (16) in order to obtain a tube having a spiral cross section. A gap (44) is defined between two ajacent la...  
WO/2017/060604A1
The invention relates to a turbine ring assembly including a plurality of ring sectors (10) forming a turbine ring (1), and a ring support structure (3) including an upstream ring-shaped flange (32) and a downstream ring-shaped flange (3...  

Matches 1 - 50 out of 8,637