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Matches 1 - 50 out of 9,306

Document Document Title
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...  
WO/2019/058069A1
The invention relates to a method for manufacturing a part using CMC, i.e. a ceramic matrix composite material, as well as such a part made of CMC, the method comprising the following steps: providing (E1) a fibrous reinforcement (10); i...  
WO/2019/057655A1
A vane assembly (100) comprising a plurality of vane units (1) and a connecting part (30), wherein each vane unit comprises a base (10) having a through-hole (12) positioned and extending between opposing longitudinal faces of the base, ...  
WO/2019/058680A1
This manufacturing method for a turbine blade comprises: a blade body divided body formation step by which blade body divided bodies that constitute the blade body of a turbine blade are formed by three-dimensional stacking; a shroud div...  
WO/2019/053229A2
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/2019/049703A1
This steam turbine blade is provided with a blade body (7) which has a blade surface (70) extending in a blade height direction. The blade body (7) has: a first suction port (74) which extends in the blade height direction and opens on t...  
WO/2019/043330A1
The invention relates to a flow-straightener vane (1) of a bypass turbomachine (100) of longitudinal axis (X), the vane (1) comprising a plurality of vane sections (2) stacked radially with respect to the axis (X) along a stacking line (...  
WO/2019/042612A1
The invetion relates to a hollow vane (100) of an output stage for a steam turbine and to a method for producing said hollow vane (100). The hollow vane (100) has an outer wall and an internal structure (110) which is arranged in an inte...  
WO/2019/045671A1
Processes and systems are described herein for forming cooling channels (314) within a ceramic matrix composite component (300). The process introducing a ceramic material (18, 32) into a solid fiber material (14, 46) to produce a cerami...  
WO/2019/044984A1
A steam turbine system (200) includes a steam turbine (60) in which a main flow path (C) through which main steam flows is formed, and a saturated steam generation unit (210) that generates saturated steam. The saturated steam generation...  
WO/2019/042970A1
A wall (1) of a hot gas component (2), comprises a hot (5) and a cold- gas sided surface (3), one film cooling hole (7) extending from an inlet (8) in the cold-gas sided surface to an outlet (9) in the hot-gas sided surface and comprisin...  
WO/2019/045891A1
A system for use in maintaining a machine including a cavity is provided. The system includes a pilot apparatus including an insertion end and a steering end opposite the insertion end. The insertion end is positionable within the machin...  
WO/2019/038500A1
Method for manufacturing a blade for a turbomachine, such as an outward guiding aerofoil blade, comprising the following steps: - arranging a first, fibrous wall preform, on a first portion of a mold (20); - placing at least one core on ...  
WO/2019/040291A1
A seal arrangement for a turbine stage includes a vane assembly including a radially inner vane platform (12), a radially outer vane platform (30), and an airfoil (28). The seal arrangement further includes a rim seal feature (14) includ...  
WO/2019/033243A1
Disclosed is a high-efficiency cooling turbine vane apparatus with dual-layered liquid-absorbing core and without opening, comprising a bulkhead outer ring (1), a turbine vane (2), a static vane retainer ring (3), rib pieces (4), and a d...  
WO/2019/034313A1
The invention relates to a mixed-flow turbine (10) for a turbocharger, comprising a turbine housing (12), with a turbine wheel (20) that is at least partially arranged in the turbine housing (12) and can be rotated in relation to the tur...  
WO/2019/030314A1
A component (300, 400) for use in a turbomachine is provided. The component (300, 400) comprises a platform (310, 410) having a leading end (312, 412) longitudinally spaced apart from a trailing end (312, 412), an aerofoil portion (320, ...  
WO/2019/027661A1
A gas turbine (10) includes a turbine section (24), and a diffuser (30) located downstream of a row of turbine blades (26) of the turbine section (24). The diffuser (30) includes an annular duct (34) extending axially along a diffuser ax...  
WO/2019/026444A1
In this gas turbine, a first stage stationary blade (23A) and a first side wall portion (54A) and a second side wall portion (54B) of a combustor outlet satisfy one of the following conditions (a) and (b). If an axial direction from an u...  
WO/2019/021027A1
A turbine housing defining a pair of volutes with respective outlets divided by a divider wall, includes a diffuser space in the gas flow path between the volutes and the turbine wheel. The diffuser space has an upstream portion having a...  
WO/2019/022862A1
A particulate-deflecting arrangement (10) for reducing ingestion of particulates into a turbine section of a combustion turbine engine is provided. This arrangement includes a deflector member (12) annularly arranged between a casing of ...  
WO/2019/015925A1
The invention relates to a method for improving the performance of a gas turbine (1), in which a hub (6) annually surrounding a rotor (2) is machined when the rotor (2) is in the non-stacked state and hot shield elements that are arrange...  
WO/2019/013178A1
The purpose of the present invention is to reduce a loss in motion energy causing rotor blades rotate, the loss being due to interference between a leakage flow at the distal end of the rotor blade and a main flow causing the rotor blade...  
WO/2019/012102A1
Compressor blade (42) for an axial compressor (10), comprising a blade root (19) and a cantilevered airfoil (20) attached to said blade root (19), the airfoil (20, 22) comprising a suction side and a pressure side extending in a span dir...  
WO/2019/009886A1
A gas turbine sealing interface (10) to seal (30) a gap between a transition duct (12) and a turbine section component is provided. The transition duct (12) includes an outlet exit frame (12, 14) including at least one fastener hole (18)...  
WO/2019/009331A1
This turbine blade comprises: a blade part; a cooling passage that extends along a blade height direction on the inside of the blade part; a plurality of cooling holes that are formed in a trailing edge part of the blade part so that the...  

Matches 1 - 50 out of 9,306