Abstract: A gas turbine includes a number of annular rotor blade rows coaxially mounted in a heating gas channel and a number of annular stator blade rows mounted between the rotor blade rows, wherein at least between two immediately adjacent stator blade rows a heat shield is positioned, which circumferentially surrounds the rotor blade row positioned between the two adjacent stator blade rows, and which has multiple ring segments, wherein at least one of the ring segments has an abrasion coating and at least one of the ring segments has no abrasion coating.

Abstract: A nickel-based superalloy is provided. Known nickel-based superalloys for producing components made of stem shaped single crystals do not provide sufficiently for grain boundary strength. The superalloy includes a low molybdenum content and very accurately adjusted values for elements having grain boundary strength and elements that precipitate in grain boundaries.

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 method of producing a component wherein a directionally solidified columnar grained cast superalloy material is heat treated such that a secondary phase of the alloy is only partly solved, thereby providing improved transverse stress rupture strength compared to fully solved alloys.

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 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: The invention relates to a method for repairing components comprising a base material with an oriented microstructure, wherein the repair point comprises a correspondingly oriented microstructure as the surrounding base material. According to the inventive method, solder is applied in the region of a point which is to be repaired and is soldered to the component by means of a heating effect produced by a device. A temperature gradient, i.e., approximately a temperature characteristic, is produced during the heating effect, said temperature characteristic ranging from a high to a low temperature in the region of the point which is to be repaired.

Abstract: A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. 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: 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: Heat treatment of alloys having elements for improving grain boundary strength Components directly after castings often reveal a low or no transverse grain boundary strength, so that cracks do appear and decrease the yield rate. The inventive measures does not lead to low transverse grain boundary strength but maintains a efficient grain boundary strength, so that the yield rate of components without cracks is increased.

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 blade for a turbine engine is described, having a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection region, to prevent local concentration of tension, such that the above borders directly on the second component piece and forms therewith a connection angle greater than 70 degrees.

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: The invention relates to a method for the production of a pattern for precision casting representation of turbine component comprising at least one cavity, whereby the prepared pattern comprises at least one core and an outer contour pattern, at least partly enclosing the core and at least partly defining the outer contour of the turbine component. The core is made from a hardening core material, which hardens during the course of the method and the outer contour pattern is made from a combustible or fusible material. The outer contour model is first produced with at least one cavity corresponding to the at least one cavity of the turbine component and subsequently, in order to form the at least one care, the hardening core material is introduced into the at least one cavity and hardened.

Abstract: The invention relates to a method for repairing components comprising a base material with an oriented microstructure, wherein the repair point comprises a correspondingly oriented microstructure as the surrounding base material. According to the inventive method, solder is applied in the region of a point which is to be repaired and is soldered to the component by means of a heating effect produced by a device. A temperature gradient, i.e., approximately a temperature characteristic, is produced during the heating effect, said temperature characteristic ranging from a high to a low temperature in the region of the point which is to be repaired.

Abstract: Heat treatment of alloys having elements for improving grain boundary strength is disclosed. Components directly after castings often reveal low or no transverse grain boundary strength, so that cracks do appear and decrease the yield rate. The provided measures do not lead to low transverse grain boundary strength but maintains efficient grain boundary strength, so that the yield rate of components without cracks is increased.

Abstract: The invention relates to a blade for a turbine engine with a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection region, to prevent local concentration of tension, such that the above borders directly on the second component piece and forms therewith a connection angle greater than 70 degrees.

Abstract: Machineable nickel base alloy casting, consisting essentially of, in weight %, about 12.5% to 15% Cr, about 9.00% to 10.00% Co, about 3.70% to 4.30% Mo, about 3.70% to 4.30% W, about 2.80% to 3.20% Al, about 4.80% to 5.20% Ti, about 0.005% to 0.02% B, up to about 0.10% Zr, and balance essentially Ni and carbon below about 0.08 weight % to improve machinability while retaining alloy strength properties after appropriate heat treatment.