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Matches 1 - 50 out of 9,384

Document Document Title
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/2019/190477A1
A sealing arrangement (10) in a gas turbine engine to seal a gap between first and second turbine components (12, 14) is provided. The sealing arrangement includes a first arcuate feather seal (16) connected to an anchoring assembly (18)...  
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/2019/174789A1
A high-performance metal alloy is disclosed being suitable for additive manufacturing of machine components, in particular machine components which are subjected to high gas temperature stress. Exemplary machine components are statoric c...  
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/2019/166742A1
Assembly for a turbomachine (1), comprising an annular channel (6) designed to form a flow duct for a flow of gas between two turbine stages (2, 3) of the turbomachine (1), said channel (6) being bounded by a radially inner annular wall ...  
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/2019/167336A1
A stator blade segment (30) is provided with: a blade ring (70); a plurality of stator blades (33); and a caulking member (90). The blade ring (70) has a blade ring groove (73) and a housing space forming part (81). The blade ring groove...  
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/2019/169280A1
A centrifugal compressor system includes a centrifugal impeller; a shroud in cooperative engagement with the impeller; and a diffuser. The diffuser has a hub surface; a shroud surface; a plurality of diffuser vanes extending between the ...  
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/2019/162601A1
The invention relates to an aircraft turbine engine (10) having a primary air flow path (16) in which a low-pressure compressor (30) and a high-pressure compressor (32) are arranged, a secondary air flow path (20) which is located around...  
WO/2019/158877A1
This relates to a turbomachine with a front-mounted fan, comprising an annular flow-splitting wall (160) provided a nose (16), for splitting an incoming air flow between a primary flow and a secondary flow, the nose having a leading edge...  
WO/2019/158854A1
The invention concerns an outer shroud (16) of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud comprising: - an annular downstream portion (24) provided with a shroud opening (30) passing through an annu...  
WO/2019/158867A1
The invention concerns a fire resistance device (50) intended to be interposed between an aircraft bypass turbine engine mounting structure (9) and a connection cowling (30) equipping this turbine engine, the connection cowling being int...  
WO/2019/157299A1
Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub...  
WO/2019/156666A1
A transition-to-turbine seal assembly, and method for manufacturing same are provided. The method allows forming an arcuate seal piece (110) including a first sealing flange (112) and a second sealing flange (114). Each sealing flange de...  
WO/2019/147219A1
Apparatus and method embodying slide on shroud cover segments for gas turbine compressor stator vanes are provided. The apparatus may include a first shroud cover segment (12) including a respective circumferential groove (14). A gas tur...  
WO/2019/141671A1
The invention relates to a molded article, such as for example a turbine component, in particular also a guide vane or rotor blade of a gas turbine, and/or a component of an exhaust gas manifold, which is made at least in part of CMC, i....  
WO/2019/138191A1
The invention relates to a lead-through arm (30) for the auxiliaries of a turbomachine, intended to be mounted in a substantially radial direction of the turbomachine. The lead-through arm (30) comprises two fairing walls (32) connected ...  
WO/2019/135838A1
This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (Wup/ W) of 0.4 to 0.7.  
WO/2019/130517A1
A steam turbine (1) is provided with a plurality of stages (ST) including stator vanes (11) and rotor vanes (13). Upstream of at least one of the stages (ST), an aperture body (35) for narrowing the passageway area of a steam passageway ...  
WO/2019/122657A1
A guide vane (15) in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis (Iz) of the vane (15) so that the differential thermal expansions compensate for the bending de...  
WO/2019/124546A1
A method for manufacturing a turbine housing in which an exhaust gas flow channel in a turbine housing is configured from a sheet-metal split body and a cast split body, a sheet-metal material being press-molded to form the sheet-metal s...  
WO/2019/117752A1
A guide vane for a wet steam turbine comprises a one-piece body. The vane is provided with internal chambers. A continuous internal chamber on the leading edge side is formed by a cavity in the one-piece body and a concave wall that form...  
WO/2019/110210A1
A heat shield (60) for a gas turbine engine (10), the heat shield (10) comprising a main body (61) having a first surface (70) and a second surface (72), the first surface (70) being exposed to a hot working gas in use, a plurality of wa...  
WO/2019/110573A1
An inlet for an axial turbine comprises a hub and a plurality of rotatable guide vanes an-anged circumferentially around the hub, the guide vanes each comprising an inner contour continuously connected by a vane surface to an outer conto...  
WO/2019/112838A1
A turbine engine having a turbine section operably connected to an exhaust section, through which an exhaust flowpath is defined. The exhaust section includes a diffuser having a diffuser flowpath. The turbine engine further includes: di...  
WO/2019/110526A1
Sector (7), made of ceramic matrix composite, of a stator (4) of a turbine (1) of a turbomachine (2) comprising an outer platform (8) and an inner platform (9) that are connected via at least one vane, said outer platform (8) comprising ...  
WO/2019/105610A1
Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an a...  
WO/2019/102205A1
A turbine comprises a housing defining a turbine chamber (52) within which a turbine wheel (14) is supported for rotation about a first axis. The housing further defines first and second inlet volutes (19a, 19b) which each spiral radiall...  
WO/2019/102170A1
Turbojet engine nacelle comprising a cascade-type thrust reverser comprising a mobile circular frame surrounding a cold air flow path, guided axially by longitudinal rails (8a, 8b) fixed to an intermediate casing (10) surrounding the col...  
WO/2019/102137A1
The invention relates to a method for producing a part of a turbomachine coated with a thermal barrier, characterised in that it comprises the following steps: (E1) producing the part by means of additive manufacturing; (E2) electrophore...  
WO/2019/097058A1
The invention relates to a steam turbine (100, 200), comprising: an inflow housing (109); nozzles (115) fixed in the inflow housing; a rotor (121) having a wheel disk (119) and wheel blades (117), a wheel intermediate space (143) lying b...  
WO/2019/097757A1
This turbine nozzle is provided with a plurality of blades that are arrayed so as to form a tapered flow path among the blades, wherein the negative pressure surface of each of the blades includes a cured surface that forms the throat of...  
WO/2019/091965A1
A turbine rear structure for a gas turbine engine which comprises primary and secondary exhaust gas guide vanes and wherein the second set of vanes are offset so as to be closer to one of the primary guide vanes than another.  
WO/2019/092679A1
The present invention relates to a method for the construction of rotor and stator elements of turbomachines, comprising: readying an ingot (1) of material to be machined; performing cuts in the ingot (1) so as to delimit blocks (10) of ...  
WO/2019/093075A1
This turbine blade is provided with a blade body and a plurality of cooling passageways which extend in a blade height direction in the blade body and communicate with each other, forming a serpentine flow passageway. The cooling passage...  
WO/2019/086065A1
The invention relates to an intermediate channel (10) for arranging between an outlet of a low-pressure compressor and an inlet of a high-pressure compressor of a turbomachine, in particular an aircraft engine, comprising an outer wall (...  
WO/2019/090018A1
A variable turbine geometry assembly (200) is provided for controlling flow of exhaust gas to a turbine wheel (110) of a turbocharger (100). The variable turbine geometry assembly (200) includes a base structure (204), vanes (202), vane ...  
WO/2019/082838A1
A shroud of this stator vane comprises a posterior passage (73n), an anterior passage (73p), and a plurality of rear-end passages (76). The plurality of rear-end passages (76) are arranged lined up in a lateral direction (Dc) between the...  
WO/2019/053229A3
The invention concerns a turbine exhaust casing (TEC) cooling arrangement for a gas turbine engine. The arrangement involves cooling the struts of a TEC using compressed air communicated from one of the engine's compressors.  
WO/2019/076519A1
The invention relates to an assembly for a turbine engine, comprising: an external housing (28) for a low-pressure compressor (4), referred to as a booster, having an annular wall (30); and an oil tank (46) having a circular internal cha...  
WO/2019/077350A1
There is provided a turbine comprising: a turbine housing; a turbine wheel; an inlet upstream of the turbine wheel, the inlet defining a first inlet portion and a second inlet portion; an outlet downstream of the turbine wheel, the outle...  
WO/2019/072407A1
The invention relates to an exhaust gas turbocharger comprising a manifold flow housing, in particular a dual flow housing (47), and a turbine wheel (34) which is rotatably arranged within this manifold flow housing, and onto which an ex...  
WO/2019/064761A1
Provided is a blade in which secondary flow loss has been reduced without changing the aerodynamic design of a base blade. This blade comprises: a base blade part; and a protruding part provided on a positive-pressure surface in the vici...  
WO/2019/063384A1
The invention relates to a diffuser for a compressor, comprising - a flow channel which is delimited in the flow direction by a first lateral wall and a second lateral wall, wherein the lateral walls run at least partly divergent relativ...  
WO/2019/058054A1
A method for producing a part from composite material comprises the following steps: - injecting into a fibrous texture (10) a slurry (BC) comprising at least one powder of refractory ceramic particles (CR) suspended in a liquid phase, -...  
WO/2019/058046A1
A method for manufacturing a part made from CMC, i.e. ceramic matrix composite material, provided with at least one cutout, and such a part made from CMC provided with at least one cutout, the method comprising the following steps: provi...  

Matches 1 - 50 out of 9,384