Method to produce a coated gas turbine component having opening holes, apparatus to perform the method and coated turbine blade having cooling holes

摘要

The method involves performing visual predetermination and storing of a surface configuration of a gas turbine component (1) i.e. turbine blade (11), for scanning a position and a shape of non-cylindrical and cylindrical film cooling holes (10) before coating the component. The surface configuration is optically three-dimensionally scanned and visually rescanned after coating the component. A tool (23) is positioned relative to the component such that the tool exposes the holes by local removal of coating material, where the positioning is carried based on the surface configuration. Independent claims are also included for the following: (1) a device for removing coating material from holes in a gas turbine component (2) a coatable turbine blade.