Abstract: The present technology generally relates to a wear-resistant coating, especially for gas turbine components, comprising a horizontally segmented or multilayered structure, i.e. at least one relatively hard, ceramic layer and at least one relatively soft, metallic layer. The ceramic layer and the metallic layer are alternately arranged on top of each other in such a way that an external layer forming an external surface of the wear-resistant coating is embodied as a ceramic layer. According to the invention, at least the external, ceramic layer is segmented in a column-type manner in a vertical direction.

Abstract: The invention relates to a method for the production of a component, especially gas turbine component, coated with a wear-protection coating, especially a corrosion-protection coating or erosion-protection coating, with the following steps: a) providing a component (10) to be coated on a component surface (13); b) at least partially coating the component (11) on its component surface with an at least two-layered or at least two-plied wear-protection coating (14), whereby the wear-protection coating (14) encompasses at least one relatively soft layer (15) and at least one relatively hard layer (16); c) surface densifying the at least partially coated component on its coated component surface.

Abstract: A method for electrochemically stripping components, especially gas turbine components, is provided. According to the method, the component from which a coating is to be removed is connected to a positive terminal of a voltage source or current source while an electrode is connected to a negative terminal thereof. An electrode is used that is precisely adapted to a region of the component to be stripped such that a gap between the region of the component to be stripped and the electrode is approximately constant over the entire region to be stripped.

Abstract: A wear-resistant coating, in particular an erosion-resistant coating for a component that is exposed to fluidic loads, is disclosed. The wear-resistant coating has one or more multilayer systems applied repeatedly to the surface to be coated, where each of the applied multilayer systems has at least four different layers. A first layer of each multilayer system facing the surface to be coated is made of a metallic material adapted to the composition of the component surface to be coated. A second layer applied to the first layer of each multilayer system is made of a metal alloy material adapted to the composition of the component surface to be coated. A third layer applied to the second layer of each multilayer system is made of a gradated metal-ceramic material and a fourth layer applied to the third layer of each multilayer system is made of a nanostructured ceramic material.

Abstract: A method and apparatus for producing a protective layer to prevent oxidation and/or corrosion for components, in particular for components of a gas turbine, are disclosed. In the method a component having a substrate surface and a substrate composition are provided. Then a coating material is supplied, where the coating material contains at least platinum and aluminum. Then the coating material consisting of at least platinum and aluminum is deposited on the component to be coated in a PVD process (Physical Vapor Deposition Process). Platinum and aluminum are deposited jointly with a single PVD process on the component to be coated.

Abstract: A protective layer for load-transferring contact surfaces of gas turbine components, especially titanium turbine components is capable to take up alternating loads at higher temperatures. The protective layer is formed of an alloy having the following composition in percent by weight: aluminum (Al) 4-8%; chromium (Cr) 2-5%; iron (Fe) 0-3.5%; and copper (Cu) remainder.

Abstract: Structural components (2), such as turbine blades (16) partially to be coated, for example with precious metal coatings, are inserted into a circumferential pocket on a carrier wheel (8), so that surface areas (10, 10A) protruding radially outwardly are presented for a coating operation, for example by vapor deposition, gas diffusion, plasma spraying, or sputtering, while surface portions (9) of the components within the wheel are protected against coating by wheel disks (8A, 8B). The wheel is rotated either continuously or stepwise through an active coating chamber (3). Surfaces to be coated participate in forming first and second walls for enclosing a coating space (11). Other walls of the space (11) are formed by one or two coating sources (12, 13), such as cathode sputterers, whereby the need for screens or masks (4, 14) that form the remaining walls of the space (11) are minimized. The bottom (59) of the space (11) is preferably formed by wall portions (4A) of the turbine blades (16).

Abstract: A process for vapor depositing a metallic interlayer on the surface of a metal component, for example, by sputtering and thereafter depositing an aluminum diffusion coating on the interlayer. The metallic interlayer is vapor deposited on the surface of the component in a noble gas atmosphere, more than one-half of which, in per cent by weight, is composed of noble gases which are heavier than argon. Advantageously, the noble gases can be krypton or xenon. The process can be used with particular advantage for applying protective aluminum diffusion coatings on turbine blades.