Abstract: The invention describes a device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Abstract: A turbine blade or vane (1) has a shell (2), including a first side wall (8) and a second side wall (9), which are connected together at a leading edge (10) and at a trailing edge (11), which extend longitudinally from a root (7) to a tip (6) and which are connected together between leading edge (10) and trailing edge (11) by a plurality of inner ribs (13). In the inner region (12) of the turbine blade/vane (1), the ribs (13) form at least one cooling gas path (15), which guides a cooling gas flow from the root (7) to the tip (6) and, in the process, is deflected a plurality of times in serpentine shape from the outside to the inside and from the inside to the outside.

Abstract: A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90°.

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: A turbine blade or vane (1) has a shell (2), including a first side wall (8) and a second side wall (9), which are connected together at a leading edge (10) and at a trailing edge (11), which extend longitudinally from a root (7) to a tip (6) and which are connected together between leading edge (10) and trailing edge (11) by a plurality of inner ribs (13). In the inner region (12) of the turbine blade/vane (1), the ribs (13) form at least one cooling gas path (15), which guides a cooling gas flow from the root (7) to the tip (6) and, in the process, is deflected a plurality of times in serpentine shape from the outside to the inside and from the inside to the outside.

Abstract: A process for producing a spatially shaped carrier layer (3) which is of foil-like design from hard brittle material includes: providing a basic mold (1) having a spatially shaped surface, depositing a material which is in the gas or liquid phase on the spatially shaped surface, solidifying the material which has been deposited on the spatially shaped surface to form a hard brittle material layer (3), and separating the hard brittle material layer (3) from the spatially shaped surface in order to obtain the carrier layer (3) which consists of hard brittle material.

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 device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Abstract: A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90°.

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 coating a base material (1) which is subject to friction with a protective layer (2) comprising MCrAlY by means of a thermal spraying process. The MCrAlY is fed to an injection nozzle in powder form and is applied to the base material (1). At the same time as the MCrAlY powder, a ceramic material in powder form, such as for example Al2O3, Si3N4, SiC, AlN, Cr3C2, MoSi2 or an equivalent material, is applied to the base material (1), a diffusion heat treatment is carried out and those locations of the applied coating (3) which are subject to friction are cut into a toothed or pointed shape.

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 device for reducing the sealing gap between a rotating component and a stationary component inside a rotary turbo-engine through which a flow passes axially and in which the rotating component and the stationary component each have a surface portion arranged separated by a sealing gap and providing sealing structures on at least one of the two surface portions, one of the sealing structures being an abradable planar sealing structure. The surface portion opposite the abradable planar sealing structure likewise has an abradable planar sealing structure, and the two sealing structures bound the sealing gap in a planar manner.

Abstract: The invention describes a temperature-stable protective coating over a metallic substrate surface (1), which coating includes at least one layer of material (4) consisting of MCrAlY, where M represents at least one of the elements selected from the group of materials consisting of Fe, Co and Ni. The invention also describes a production process for this coating.

Abstract: A cooled gas turbine blade with a shroud in which a cooling channel system is provided, which is closed off radially to the gas turbine blade with a cover plate is characterized in that the cover plate has a circumferential edge, along the entire extension of which the cover plate enters into a continuous shape-mated connection or a plurality of locally limited shape-mated connections with the shroud.

Abstract: The invention describes a temperature-stable protective coating over a metallic substrate surface (1), which coating includes at least one layer of material (4) consisting of MCrAlY, where M represents at least one of the elements selected from the group of materials consisting of Fe, Co and Ni. The invention also describes a production process for this coating.

Abstract: The invention relates to a method for repairing a superficial damaged area in a metal component formed as a result of a loss of material, whereby the damaged area is filled by way of a high-temperature soldering process. In order to improve the durability of the filling, an active solder is used during the high-temperature soldering process.

Abstract: 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. During the coating a mass flow (10) emerges through the cooling-passage opening (1), the coating takes place by a coating mass flow (11) directed onto the surface (12) which is to be coated, and the mass flow (10) emerges through the cooling-passage opening (1) and the coating mass flow (11) include an angle &agr;≠0°.

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: A method of fitting an impingement plate to a platform of a guide blade of a gas turbine. The impingement plate is first fastened at individual spots by spot welds to at least one supporting surface of the platform and is then brazed at the supporting surface to the platform. The impingement plate is prefabricated with recesses and the spot welds are executed at the recesses.