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WO/2016/111249A1 |
Provided are an austenite-based heat-resistant steel and a turbine component, which have a reduced linear expansion coefficient while maintaining high-temperature creep strength, and with which satisfactory weldability can be ensured. Th...
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WO/2016/110342A1 |
A blade (20) for a rotor (15) of a gas turbine (10) comprises: - a root (22), - a platform (24) having a lower surface (31) and an upper surface (30) opposite to the lower surface (31), - a hollow aerofoil (26), - an inner cooling passag...
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WO/2016/111773A1 |
A metal insert tube (460) of a turbine vane (452) is disclosed. The insert tube (460) includes a pressure side wall (461), a suction side wall (464) opposite and spaced apart from the pressure side wall (461), a leading edge (462), and a...
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WO/2016/110364A1 |
The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an ...
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WO/2016/110387A1 |
The invention relates to a film-cooled gas turbine component (8) for a gas turbine, comprising a surface (38) which can be exposed to a hot gas (39) and in which a number of film-cooling openings (36) end, wherein each of the film-coolin...
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WO/2016/107710A1 |
The invention relates to a thermocouple (2, 2a-e), comprising a first conductor (4, 4a-c), consisting of a first conductor material (6, 6a, 6b), and a second conductor (8, 8a-c), consisting of a second conductor material (10, 10a, 10b), ...
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WO/2016/102839A1 |
The invention relates to a method for manufacturing a fibrous preform filled with refractive ceramic particles (20), comprising the following steps: a) placing a fibrous structure comprising refractive ceramic particles into a mould cavi...
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WO/2016/105490A1 |
A turbine blade has an undercut beneath its platform proximate a trailing edge region. The undercut incorporates a curved portion to reduce to reduce undesirable stress concentration. The undercut shape includes a curved portion of decre...
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WO/2016/102858A1 |
The invention relates to a method for producing a turbomachine part by means of a laser process. According to the invention, a part is made by means of a laser beam, with a nozzle (1) that sprays a metal powder towards a substrate (5). I...
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WO/2016/105327A1 |
A method for reducing defects on a component (105) having at least a substrate (116), a thermal barrier coating layer (112) over the substrate (116), and cooling holes (100) through the substrate and the thermal barrier coating layer (11...
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WO/2016/102100A1 |
The invention relates to an expansion machine (20), comprising an output shaft (24) and a shaft sealing ring (25) that interacts with the output shaft. The expansion machine (20) has an inflow region (21) and an outflow region (22). Duri...
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WO/2016/102837A1 |
The invention relates to a method for manufacturing a part made of composite material, which includes the following steps: forming a fibrous texture (10) from refractory fibres; placing the fibrous texture (10) in a mould (110) including...
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WO/2016/102128A1 |
The invention relates to a radial compressor for a turbocharger, in particular of an internal combustion engine, and to a turbocharger comprising such a radial compressor. The invention further relates to a method for operating such a ra...
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WO/2016/097632A1 |
The present invention relates to a turbine assembly (10) of a turbine engine (1), comprising at least: a first bladed rotor (12), a bladed stator (13) and a second bladed rotor (14) arranged in series, the rotors (12, 14) being mounted o...
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WO/2016/097053A1 |
In a method for machining a workpiece by means of a machining tool, it proposed that the workpiece (1, 20) is held in a workpiece bracket (2) and a stabilizing device (5, 21) is secured in a friction-locking and/or interlocking manner to...
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WO/2016/097586A1 |
The invention relates to a method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, said blade (25) comprising a t...
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WO/2016/099662A2 |
An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cool...
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WO/2016/097597A1 |
The invention relates in particular to a method (100) for repairing a fan casing (10) in which the inner surface (12) is damaged (11). The method (100) comprises a step (102) of attaching a reinforcement element (13) to the fan casing (1...
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WO/2016/096420A1 |
The invention relates to a diversion guide device (26) in the labyrinth seal (25) in the large intermediate base (19) for diverting the leakage steam in the circumferential direction (28) in order to thereby obtain a cooling effect in th...
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WO/2016/096382A1 |
The invention specifies a method (1) for repairing damage (2) to a turbine blade (4), there being provided a predefined template (12c) which completely covers at least the damage (2), wherein in the region of the damage (2) the material ...
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WO/2016/099663A2 |
An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The wall includes one or more film holes that have an outlet provi...
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WO/2016/093811A1 |
A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each...
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WO/2016/090405A1 |
A method of forming a fibre metal composite component. The method includes the steps of forming a substantially elongate metal skin (22) with a hollow interior of a first volume and open opposed first (22a) and second ends (22b). The sec...
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WO/2016/087140A1 |
The invention relates to a method for producing a rotor blade (120) for a gas turbine (100), the blade having a fastening region (162) and a platform (160), on which a blade (166) ending in a blade tip (167) is arranged. The aim of the m...
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WO/2016/087293A1 |
What is provided is a turbine blade (1) having a blade geometry defined in a coordinate system and at least one cavity (9, 15) which is open to the outside and which has a blade internal surface (10, 18, 19). At least one planar detectio...
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WO/2016/087153A1 |
The invention relates to a rotor (R), of a multi-staged axial compressor (ACO), which extends along an axis of rotation (X), wherein the rotor (R) has a shaft (SH), wherein the shaft (SH) has rotor blade slots (RBG), wherein rotor blades...
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WO/2016/089970A1 |
A vane (110) for an Inlet Guide Vane (IGV) (112) of a multistage compressor (100) includes a root portion (114), a tip portion (116), and an airfoil (118) extending therebetween. The vane (110) is configured such that a ratio of the maxi...
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WO/2016/087766A1 |
The invention relates to a method for manufacturing a part (1) coated with a protective coating (2) comprising the following step: - formation of a protective coating (2) across all or part of the surface (S) of a part (1), wherein the p...
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WO/2016/088833A1 |
A sprayed-coating formation method equipped with: a step for preparing a spray target member having a surface in which one end of a plurality of holes opens; a step for preparing a plurality of masking pins comprising a metal; an inserti...
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WO/2016/087154A1 |
The invention relates to a method for repairing a component (1), comprising the following steps: introducing a recess (2) into the component (1), via which recess a damaged region in the component (1) is removed; positioning a filler bod...
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WO/2016/087215A1 |
The invention provides a method (2) for coating a turbine blade (1), which comprises an aerofoil (4) and at least one platform (2) arranged at one end of the aerofoil (4), wherein the or each platform (2) has a contact zone (6) and at le...
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WO/2016/087214A1 |
A turbine blade (120) for a turbomachine (100) comprises a fastening section (154) and an adjoining platform (152) on which a blade (144) having a profiled cross-section is arranged, said blade (144) ending at a blade tip. The aim of the...
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WO/2016/087143A1 |
By continuously long engravings the spallation behavior of the thermal barrier coating is reduced and the lifetime of the TBC is prolonged.
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WO/2016/087337A1 |
The aim of the invention is to provide a method for producing and repairing a turbine blade (120) comprising vibration dampers (156) for a gas turbine (100) that allows a particularly high efficiency of the gas turbine at the same time a...
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WO/2016/085654A1 |
A hybrid component (45) is provided including a plurality of laminates (10) stacked on one another to define a stacked laminate structure (58). The laminates (10) include a ceramic matrix composite material (22) having certain features s...
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WO/2016/086122A1 |
Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper i...
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WO/2016/086117A1 |
The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the...
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WO/2016/085260A1 |
An embodiment of the present invention provides a turbine apparatus comprising: a shaft; a turbine disk which is provided on the shaft and has formed thereon a plurality of protruding portions protruding in the direction of the shaft; bl...
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WO/2016/086121A1 |
The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the...
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WO/2016/078927A1 |
Disclosed is a gas turbine unit (100) comprising: a compressor section (105); a combustion chamber section (106) containing at least one combustion chamber (110); and a turbine section (108), wherein, starting from a compressor inlet, a ...
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WO/2016/078980A1 |
The invention relates to an exhaust-gas section (12) for a gas turbine (1), comprising a surrounding shroud (42, 44) having a first opening (48), which is arranged in a region of the exhaust-gas section (12) that has a pressure lower tha...
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WO/2016/081107A1 |
A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includ...
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WO/2016/078537A1 |
A power device, comprising an impeller (20) connected to a rotating shaft (5), and a fan blade (21) provided at a periphery of the impeller (20); a casing (32) of the fan blade (21) is sequentially provided with an outer-layer fluid chan...
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WO/2016/080136A1 |
This turbine rotor blade (26) used for a turbine is provided with: an airfoil section (30) which has an airfoil shape formed by a ventral surface (31) and a dorsal surface (32); and one or more squealer ribs (40, 42, 44) which are dispos...
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WO/2016/079743A1 |
A pressurized, fluid-filled channel network embedded in an elastic structure, asymmetrically to the neutral plane, is used to create a deformation field within the structure by the pressurization of the embedded fluidic network, which ca...
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WO/2016/078851A1 |
The invention relates to a hollow blade body for a hollow blade (1), comprising a blade wall (6) which has a pressure side (4) which has at least one first blade connection element on the inner side (9) thereof, and a suction side (5) wh...
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WO/2016/080025A1 |
An axial-flow-machine blade according to the present invention is provided with: a blade body (39) that extends in a radial direction; a platform (end wall)(41) that is provided at an end section (40) of the blade body (39) in the radial...
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WO/2016/076374A1 |
A rotor assembly for a turbine, provided with a rotor shaft and a plurality of blades, the rotor shaft having: two protruding parts; two bearing surfaces; two first opposing surfaces that constitute a portion of a wall surface of a blade...
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WO/2016/076750A1 |
The invention relates to the field of power plant engineering and thermal power engineering and can be used in developing steam-turbine power installations. A turbine-generator shaft train contains rotors of a multi-cylinder steam turbin...
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WO/2016/075391A1 |
According to the invention, a blade (12') is friction-welded to a rotor disk (10') of a turbomachine, the disk comprising a projecting block (18) having an outer surface to which the blade (12') is to be welded. To this end: a surfacing ...
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