Abstract: A method and apparatus for the detection of flaws, in particular of fissures, in metal components, is disclosed. A pulsed high-frequency magnetic field is coupled to the component. The temperature distribution of thermal energy generated by eddy currents during the application of a magnetic field pulse is detected.

Abstract: A gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade and a vane footing. The blade is defined by a flow inlet edge or a front edge, a flow outlet edge or a rear edge, and a blade surface extending between the front edge and the rear edge and forming a suction side and a pressure side. The suction side of the blade includes at least one microprofiled or microstructured region for optimizing the flow around the blade.

Abstract: The invention relates to a method to manufacture components or semi-finished parts for gas turbines, in particular for aircraft engines, preferably by casting. According to the invention, a smelting crucible that is manufactured of boron nitride is Used (FIG. 1).

Abstract: The invention relates to a composite material which is formed of several assembled discs of matrix material, wherein preferably in each disc at least one groove is formed in which at least one fiber (14) is inserted. According to the invention a composite of matrix material and fiber (14) is present in an inner section (16), whereas the matrix material is exclusively present in an outer section (17), wherein the fibers (14) reach to different extents into the outer section (17), in which the matrix material is exclusively present, for a strength optimizing intermeshing of the inner section (16) with the outer section (17).

Abstract: Two structural components, such as a gas turbine rotor hub and a rotor blade, are integrally joined to each other by friction welding, particularly linear friction welding. For this purpose, each component is provided with a joining surface and at least one of the two components is provided with a groove next to the respective joining surface. The groove extends fully or partly around the respective joining surface and serves for reducing stress in a normal and radial direction of the respective joining surface, whereby a more uniform heating of the joining zone is achieved and joining faults are avoided or at least reduced during the friction welding.

Abstract: A method for producing a component and/or a coating from a vibration-damping alloy or intermetallic compound includes producing the component and/or the coating via thermal spraying.

Abstract: A process for the manufacture of a thermo-mechanically stable thermal insulating layer, in which a ceramic thermal insulating layer is applied to a metallic component by thermal spraying and the thermal insulating layer is shot peened during and/or after its application in order to reduce sintering effects. The ceramic thermal insulating layer has a porous structure which is opened up by the formation of microscopic fissures formed near the surface of the layer by the shot peening.

Abstract: A ceramic heat insulation layer applied to a metal structural part or to an intermediate adherent layer thereon, has the surfaces of its inner, open pore structure coated with a passivating ceramic material or a metal deposition material for improving the properties of the heat insulation layer.

Abstract: A ceramic heat insulation layer applied to a metal structural part or to an intermediate adherent layer thereon, has the surfaces of its inner, open pore structure coated with a passivating ceramic material or a metal deposition material for improving the properties of the heat insulation layer.