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Matches 1,101 - 1,150 out of 23,225

Document Document Title
WO/2016/113041A1
The invention relates to a method for mounting rotor blades (1) on a rotor disk (2) along a predetermined pitch circle diameter (D) in such a way that adjacent rotor blades (1), when properly mounted on the rotor disk (2) and in the cold...  
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...  
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...  
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...  
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 ...  
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...  
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), ...  
WO/2015/091289A3
The invention refers to a method of assembling or disassembling a rotor blade (100) or guide vane assembly, wherein the rotor blade or guide vane comprises an airfoil (110) and additional structured peripheral members forming at least an...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
WO/2015/081037A8
According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while a...  
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...  
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...  
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 ...  
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...  
WO/2015/130526A3
Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensi...  
WO/2015/130521A3
Cooling holes in a turbine component, such as a blade, vane or combustor transition, are formed in and surrounded by a micro surface feature (MSF) that protects the adjoining thermal barrier coating (TBC) from delamination or crack propa...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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.  
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...  
WO/2015/191330A8
A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor bla...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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...  
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...  
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...  

Matches 1,101 - 1,150 out of 23,225