Abstract: Provided is a method for the non-destructive material testing of a component that defines a receptacle groove for the blade root of a blade of an axial turbomachine, the component in particular being a shaft of a turbine or of a compressor, or of a rotor disk that is provided on the shaft, and of a blade root of a blade, wherein the testing head of a testing apparatus for non-destructive material testing in the assembled state is disposed in an intermediate space formed in the region of the receptacle groove between the component that defines the receptacle groove and the blade root, and in particular is displaced in the intermediate space, and the component that defines the receptacle groove and/or the blade root by way of the testing head that is disposed in the intermediate space are/is examined in a non-destructive manner for material faults.

Abstract: The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.

Abstract: The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.

Abstract: The invention relates to a process for producing a protective layer on a bolt, in which an aluminum-containing high-temperature lacquer is first of all applied to the bolt and then cured and stoved at a defined stoving temperature. The screw thread is additionally lubricated prior to installation of the bolt. This process reduces oxidation and ultimately reduces seizing of the screw connection.