Patent application number | Description | Published |
20100124493 | MULTI-VANE SEGMENT DESIGN AND CASTING METHOD - Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud. | 05-20-2010 |
20100166563 | METHOD FOR IMPROVING THE SEALING ON ROTOR ARRANGEMENTS - A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described. | 07-01-2010 |
20110016875 | GUIDE VANE HAVING HOOKED FASTENER FOR A GAS TURBINE - A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer platform, the inner side of which is exposed to the hot gas which flows through the gas turbine, and on which provision is made for a hook-like fastening element, projecting outwards in the region of the trailing edge, for fastening the stator vane on a casing of the gas turbine, which fastening element, on its side facing the trailing edge, has a locating slot above the trailing edge for the fixing of a heat shield which adjoins the outer platform of the stator vane in the flow direction of the hot gas. With such a stator vane, the service life can be extended by provision being made on the outer platform of the stator vane between the locating slot and the trailing edge of structure for reducing the thermal and mechanical stresses in the region of the transition between trailing edge and outer platform. | 01-27-2011 |
20110058957 | BLADE FOR A GAS TURBINE - A blade is provided for a gas turbine, especially for the low-pressure turbine of a gas turbine with sequential combustion, and is produced in accordance with a casting process and has a blade airfoil which extends in the radial direction between an inner platform and an outer platform, and in the interior of which extends a cooling passage, bypassing the platforms, and through which flows a cooling medium, especially cooling air, for cooling the blade. In the outer and/or inner platform there are core outlet openings which arise from the use of a casting core and which connect the cooling passage to the outside space and are sealed off by means of a sealing element. Optimum cooling is ensured by the sealing elements being formed and inserted into the core outlet openings so that they align with the wall surface of the cooling passage in a flush manner. | 03-10-2011 |
20110189002 | TURBINE GUIDE VANE - A turbine guide vane ( | 08-04-2011 |
20110243756 | METHOD FOR PRODUCING A BLADE BY CASTING AND BLADE FOR A GAS TURBINE - A method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a single cooling air channel running in the blade longitudinal direction from the blade root to the blade tip. The method includes, during the casting of the blade, the blade material being fed exclusively from the blade root into the mold provided therefor, and the cooling air channel is formed during the casting of the blade by using a single core body, which is provided, at the blade tip, with a local casting cross section increasing element. | 10-06-2011 |
20110286834 | GUIDE VANE FOR A GAS TURBINE - A guide vane is provided for a gas turbine and has an airfoil extending in the radial direction between an inner platform and an outer platform. The airfoil extends transversely to the direction of the hot gas flow between a leading edge and a trailing edge and has a pressure side and a suction side. A cooling slot running parallel to the trailing edge is provided on the pressure side in front of the trailing edge, a cooling medium can exit through the cooling slot from the guide vane over the entire length of the guide vane and can cool the trailing edge of the guide vane. In such a guide vane, the service life is extended by a thermal stress reducing element provided on the inner platform below the trailing edge and the cooling slot. | 11-24-2011 |
20110286849 | BLADE FOR A GAS TURBINE - A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width. | 11-24-2011 |
20140030077 | STATIONARY GAS TURBINE ARRANGEMENT AND METHOD FOR PERFORMING MAINTENANCE WORK - The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means. | 01-30-2014 |
20150037167 | TURBINE BLADE AND TURBINE WITH IMPROVED SEALING - The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine. | 02-05-2015 |