Abstract: The invention relates to a gas turbine seal, comprising a metallic component (1) with a durable or erosion-resistant ceramic coating (2) and an abradable ceramic layer (18) which is arranged thereon in locally delimited fashion, a bond layer (5) being arranged on the surface (4) of the metallic component (1), to which bond layer the durable or erosion-resistant ceramic coating (2) is applied as a covering layer. The invention is characterized in that the bond layer (5) comprises separate, adjacent spherical rivets (6) or mushroom-shaped rivets (6) which have a web (7) and a head (8). These rivets form individual metal islands with numerous undercuts (12), around which there is a continuous ceramic network. It is possible to produce very thick layers which have a good bond strength, the ceramic not being flaked away even in the event of introduction of radial/tangential forces, sickle-shaped contact or locally high overheating/frictional heat, and a good sealing action being achieved.

Abstract: Described is a cooling device for a shroud of a gas turbine blade, having a cooling channel system provided in the shroud, which is provided radially to the gas turbine blade with cooling channels that are open on one side, and which is closed off with a cover plate. The invention is characterized in that, between the cover plate and the cooling channels that are open on one side, an impact cooling plate is provided in such a way that the impact cooling plate rests on the cooling channels that are open on one side, is pressed against them by force, and encloses a space with the cover plate.

Abstract: The process according to the invention discloses production of a high-quality insulation for conductors or conductor bundles. In this process, internal corona-discharge protection, insulation and external corona-discharge protection are all applied to the conductor or conductor bundle in successive steps by means of thermal spraying. The application thickness per spraying run is up to 0.2 mm, thus ensuring that the layer is free of defects and therefore avoiding partial discharges. Moreover, the ability to withstand thermal loads is considerably improved by the use of high-temperature plastics with fillers comprising inorganic materials as coating powder.

Abstract: The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.

Abstract: A method of fitting an impingement plate (5) is disclosed, the impingement plate (5) being brazed to a platform (2) of a guide blade (1) of a gas turbine. The impingement plate (5) is first fastened at individual spots by spot welds (7) to at least one supporting surface (10) of the platform (2) and is then brazed at the supporting surface (10) to the platform (2). The impingement plate (5) is prefabricated with recesses (8) and the spot welds (7) are executed at the recesses (8).

Abstract: The invention describes a process and a device for coating a temperature-stable component with a thermal protection layer (15), in which the temperature-stable component has a surface (12) which is to be coated with the thermal protection layer (15) and at which there is at least one cooling-passage opening (1) which is connected to a cooling passage running inside the component.

Abstract: A base material (2) with a cooling air hole (1) is disclosed, means being present which prevent particles (5), which are located in the cooling air (4) which flows through the cooling air hole (1) during the operation of the cooling air hole (1), from closing the cooling air hole (1). In this arrangement, the means can consist in the edge of the cooling air hole (1) being uneven or having a ridge (3) or the cooling air hole (1) being star-shaped, ellipsoidal or linear or the cooling air hole (1) being circular and having lateral slots (7).

Abstract: The invention describes a process for producing a spatially shaped carrier layer (3) which is of foil-like design from hard brittle material.

Abstract: In a soldering process for treating tears, recesses, or other material defects in the surface of thermally and mechanically highly stressed components of gas turbines, a nickel foam is applied together with the soldering powder, which can also be mixed with another filler. After this, a heat treatment of the soldering process is performed.

Abstract: The invention relates to a process for producing sandwich structures (1) between metallic and nonmetallic materials, in which a bond layer (3) is applied to a surface (10) of a metallic base body (2), a nonmetallic material (5) is then applied to the bond layer, and in which the bond layer (3) is produced from individual welded-on rivets (4) which have a mushroom-like shape with web (8) and head (9). The process is characterized in that the mushroom-shaped rivets (4) are prefabricated in a first process step, in a second process step these rivets (4) are sorted for mechanical further processing, oriented and introduced into a welding unit (15) in such a manner that in a third process step the rivets (4) are successively welded, in each case by means of the free end of their web (8), onto the surface (10) of the base body (2), thereby forming anchor points for the nonmetallic material (5). The invention also relates to the sandwich structures (1) produced using the process.

Abstract: The invention relates to a sandwich structure (1) between metallic and non-metallic materials, in which a bond layer (3) is arranged on one surface (10) of the metallic material, which forms a base body (2), to which bond layer the non-metallic material (5), preferably ceramic material, is applied as a covering layer, and the bond layer (3) comprises separate, adjacently arranged spherical rivets (4) or mushroom-shaped rivets (4) which have a web (8) and a head (9). According to the invention, the rivets (4) are cast at the same time as the base body (2). They form individual islands of metal, around which there is a continuous ceramic network, which has a positive influence on the properties of the sandwich structure.

Abstract: Described is a cooling device for a shroud (1) of a gas turbine blade, having a cooling channel system provided in the shroud (1), which is provided radially to the gas turbine blade with cooling channels (4) that are open on one side, and which is closed off with a cover plate (2),

Abstract: In a method of processing and identification of information, documents are processed in the form of hierarchically structured information units. Characteristic graphic elements are in particular shown in an overview representation. In this manner, the information content of a document can be grasped more rapidly and more accurately than by keyword searches.

Abstract: Described is a cooled gas turbine blade with a shroud (2) in which a cooling channel system (K) is provided, which is closed off radially to the gas turbine blade with a cover plate (6).

Abstract: A device is described for reducing the sealing gap between a rotating component and a stationary component (1, 2) inside a rotary turbo-engine through which a flow passes axially and in which the rotating component (1) and the stationary component (2) each have a surface portion (3, 4) arranged separated by a sealing gap (5) and providing sealing structures on at least one of the two surface portions (3, 4), one of the sealing structures being an abradable planar sealing structure.

Abstract: The invention relates to a method for repairing a superficial damaged area (2) in a metal component (1) formed as a result of a loss of material, whereby the damaged area (2) is filled by way of a high-temperature soldering process.

Abstract: A thermally highly loaded casting is produced. The casting mold is produced from a slurry using a wax model and a polymer foam which is fixed to the wax model or has been introduced into a cavity. In this way, during the casting process the liquid superalloy also penetrates into the open-cell structure of the casting mold, so that an integral cooling structure is formed during the solidification of the casting. A single-crystal or directionally solidified casting is advantageously produced. It is also conceivable to vary the cell size of the polymer foam, to produce a cooling structure and a base material separately, and to coat the cooling structure with a ceramic protective layer (thermal barrier coating).

Abstract: A winding bar (10) for a high-voltage winding, for example a stator winding of an electric machine, includes a plurality of conductors (13) which are arranged above and/or next to one another in a conductor bundle. The conductor bundle has a rectangular cross section. The conductor bundle is surrounded by an insulation (14). An overall improved electric strength is achieved at the edges without changing the insulation thickness because a thickness (d2) of the insulation (14) on the edges (15) of the winding bar (10) is greater than the thickness (31) of the insulation (14) on the flat sides of the winding bar (10). Preferably, a calibration process is used to shape the edge region.

Abstract: To produce a thermally highly loaded casting (1, 14, 16, 17) of a thermal turbomachine which is produced using a known casting process, the casting mold is produced from a slurry using a wax model and a polymer foam which is fixed to the wax model or has been introduced into a cavity. In this way, during the casting process the liquid superalloy also penetrates into the open-cell structure of the casting mold, so that an integral cooling structure (7) is formed during the solidification of the casting (1, 14, 16, 17). A single-crystal or directionally solidified casting (1, 14, 16, 17) is advantageously produced. It is also conceivable to vary the cell size of the polymer foam, to produce cooling structure (7) and base material separately and to coat the cooling structure (7) with a ceramic protective layer (thermal barrier coating) (11).

Abstract: In a soldering process for treating tears, recesses, or other material defects in the surface of thermally and mechanically highly stressed components of gas turbines, a nickel foam is applied together with the soldering powder, which can also be mixed with another filler. After this, a heat treatment of the soldering process is performed.