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Matches 1 - 50 out of 8,383

Document Document Title
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...  
WO/2017/058694A1
A spiral cooling system for cooling an aft turbine casing of a gas turbine engine. The gas turbine engine includes a turbine casing having a fore end and an aft end, a star bearing support member supporting a bearing housing and includin...  
WO/2017/058155A1
Provided is a way of implementing impingement cooling for a gas turbine engine. Instead of welding the impingement sheets (10a-10i) to an integrated exit piece (15), the impingement sheets (10a-10i) are attached in a way that takes advan...  
WO/2017/052794A3
The present invention discloses a novel apparatus and methods for providing a flow of cooling air to one or more turbine nozzles or turbine blade outer air seals. The flow of cooling air is provided by an external source and regulated in...  
WO/2017/051346A1
This disclosure describes an improved method of electron beam ("EB") welding utilizing a collection pocket (118). The method includes providing a first surface (110,146) and a second surface (100,132,140,144), forming a collection pocket...  
WO/2017/045809A1
The invention relates to a gas turbine guide vane segment (1) and the corresponding method of manufacturing. The gas turbine guide vane segment (1) comprises a first guide vane part (2) comprising an aerofoil (21) and a first platform se...  
WO/2017/046534A1
The invention relates to a nozzle sector (22) for a turbine engine. The nozzle sector comprises a radially outer platform (24), a radially inner platform (26), a first end blade (81), a second end blade (84) and at least one first centra...  
WO/2017/047516A1
The objective is to enable the portion of a combustor tube where the temperature rises to be cooled efficiently, and to improve the reliability of a combustor tube without reducing the efficiency of a gas turbine. Therefore, this combust...  
WO/2017/048149A1
The invention relates to the energy sector. A device for converting the energy of a drop in the pressure of a gaseous working fluid comprises a housing, a consumer of the mechanical energy generated, and an expansion turbine with a blade...  
WO/2017/042448A1
Casing for rotary machines, in particular for turbomachines, comprising a chamber (2) intended to house a turbine, and a gas circulation duct (3) opening into said chamber, the casing having at least one cavity (4) surrounding at least p...  
WO/2017/039567A1
A combustor transition duct (110) comprising a main duct portion (113) having a primary opening and a secondary opening, wherein a first axis extends from a center of the primary opening to the secondary opening; an extension flange (115...  
WO/2017/037399A1
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...  
WO/2017/029689A1
The turbine (21) is equipped with: a casing (30); a turbine rotor (90) which is disposed inside the casing (30) so as to penetrate therethrough; rotor vanes (100) which are implanted along the circumference of the turbine rotor (90); an ...  
WO/2017/029090A1
The invention relates to a tubular combustion chamber (22) for a gas turbine (1), comprising at least one burner arrangement (11), a housing wall (24) which surrounds the combustion chamber interior and has a flame tube (20) and a transi...  
WO/2017/025995A1
A turbine blade (120), a plurality of which are arranged in a row in an annular flow path in an axial-flow turbine, is provided with: a dorsal surface (106) which curves in a convex shape; a ventral surface (107) on the opposite side to ...  
WO/2017/026314A1
A shroud of a stationary blade (50) has formed therein a plurality of circumferential ejection passages (95) that connect with a cavity (69) into which cooling air (Ac) flows and that open on a circumferential end surface (63). Of a cent...  
WO/2017/023325A1
A trailing edge duct (110) is used with gas turbine engines. The trailing edge duct (110) is unitary in shape and has improved aerodynamics. The trailing edge duct (110) has a trailing edge (120) that is able to provide improved support ...  
WO/2017/021067A1
The invention relates to a turbomachine, in particular a steam turbine (2) having an overload inflow region (17) which is designed for the inflow of overload steam, wherein said overload steam is prevented from impinging on the rotor sur...  
WO/2017/023328A1
A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion b...  
WO/2017/023327A1
A combustor has a trailing edge duct (110) that has cooling features located at various locations. The cooling features comprise pockets (125) that have pocket channels (127) which extend from the pockets (125) to seam locations on the m...  

Matches 1 - 50 out of 8,383