Abstract: Process and apparatus for producing a turbine component, turbine component and use of the apparatus Turbine components have to withstand high thermal and mechanical loads. It therefore proves advantageous for them to be made from a material with a preferred crystal orientation. Hitherto, the turbine components with a preferred crystal orientation have been produced as a single piece, with relatively high scrap rates. The proposed concept makes it possible to produce a preferred turbine component (9, 10) in a particularly simple way by assembling a turbine component (9, 10) at least from a first base part (1) and a build-up material (8), the subregion (7) of the joining zone having a preferred crystal orientation (2), so that disadvantageous properties of a joining zone without a preferred crystal orientation (2) which have hitherto been encountered are avoided.

Abstract: There is described a turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by means of a high-temperature high-pressure bonding process and, under certain circumstances, may come apart at the blade tip. In order to prevent this, in the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.

Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Abstract: A system and method for reconfiguring a turbine vane. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by fixing portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane, restricting other portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane to only move rotationally about a centerline of the inner or outer shrouds, and applying a load to various portions of the inner and outer shrouds and the airfoil to return the turbine vane to be within predetermined specifications.

Abstract: Methods according to prior art for producing three-dimensional molded bodies generally require outer molds which define the geometry of a component to be produced. The inventive method for producing three-dimensional molded bodies renders one such mold redundant. The geometry of a component to be produced is defined by a pre-determined laser guidance or by the geometry of the partial quantities used.

Abstract: A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Abstract: A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.

Abstract: On account of their type of coating, layer systems of the prior art often exhibit poor adhesion to the substrate. If the components are subject to high mechanical stresses, the layer can then become detached. The layer system according to the invention has separately produced anchoring means which allow stronger attachment to the substrate than the attachment of the outer layer to the substrate.

Abstract: In the case of the epitaxial growth according to the prior art, a number o strips often have to be produced in a plane in order to restore an area to be repaired. This leads to overlapping and misorientation of the crystalline structures. In the case of the method according to the invention, the strip is of such a width that no overlapping occurs, since the width is adapted to the contour of the area to be repaired.

Abstract: Components comprising corrosion products are often reused, in which case the corrosion product has to be removed. According to the prior art, this takes a very long time since the reaction times with the corrosion product are often very long. According to the invention, the corrosion product is pretreated in order to produce a larger attackable surface area, so that the corrosion product can be removed more quickly.

Abstract: According to the prior art, through-holes in components are often introduced after the production (casting) of the component. This entails additional outlay in terms of time and equipment. The time required can be considerably shortened if a casting mold is designed in such a way that the through-hole is at least in part formed by corresponding projections being formed on the inner wall and/or the outer wall of the casting mold.

Abstract: Previous methods for the production of a hole in a component are very time-consuming and expensive, as special lasers having ultra short laser pulse lengths are used. The inventive method varies laser pulse lengths and ultra short laser pulse lengths are used exclusively in the region which is to be removed, wherein it is possible to have a noticeable influence on through flow and/or out-flow behavior. This, for example, the inner surface of a diffuser of a hole, which can be produced in a precise manner using ultra short laser pulse lengths.

Abstract: On account of their form of coating, layer systems according to the prior art often only have a low level of attachment to the substrate. The layer may then become detached in the event of high mechanical loads being applied to the components. The layer system according to the invention has separately produced anchoring means which are more strongly attached to the substrate than the attachment of the layer to the substrate.

Abstract: On account of their type of coating, layer systems of the prior art often exhibit poor adhesion to the substrate. If the components are subject to high mechanical stresses, the layer can then become detached. The layer system according to the invention has separately produced anchoring means which allow stronger attachment to the substrate than the attachment of the outer layer to the substrate.

Abstract: According to prior art, structural errors in substrates in epitactic crystal growth are often carried over from the substrate on which the new material is to be deposited. This leads to a reduction in mechanical properties. According to the method, an intermediate layer is deposited prior to the deposition of epitactic material. Said intermediate layer prevents structural errors in the substrate from being carried over to the newly filled area.

Abstract: According to the prior art, passage holes in components are often introduced after the operation (casting) for producing the component. This signifies an additional outlay in terms of time and of apparatus. The outlay in terms of time can be reduced considerably if a casting mold is formed in such a way as at least partially to produce the passage hole, in that projections corresponding to the passage holes are formed on the inner wall and/or the outer wall of the casting mold.

Abstract: On account of their type of coating, layer systems of the prior art often exhibit poor adhesion to the substrate. If the components are subject to high mechanical stresses, the layer can then become detached. The layer system according to the invention has separately produced anchoring means which allow stronger attachment to the substrate than the attachment of the outer layer to the substrate.

Abstract: According to the prior art, through-holes in components are often introduced after the production (casting) of the component. This entails additional outlay in terms of time and equipment. The time required can be considerably shortened if a casting mold is designed in such a way that the through-hole is at least in part formed by corresponding projections being formed on the inner wall and/or the outer wall of the casting mold.

Abstract: Methods according to prior art for producing three-dimensional moulded bodies generally require outer moulds which define the geometry of a component to be produced. The inventive method for producing three-dimensional moulded bodies renders one such mould redundant. The geometry of a component to be produced is defined by a pre-determined laser guidance or by the geometry of the partial quantities used.

Abstract: On account of their form of coating, layer systems according to the prior art often only have a low level of attachment to the substrate. The layer may then become detached in the event of high mechanical loads being applied to the components. The layer system according to the invention has separately produced anchoring means which are more strongly attached to the substrate than the attachment of the layer to the substrate.