| 摘要 |
The invention relates to a method for producing a gas turbine vane, comprising the following steps: producing, especially casting, a hollow, supporting metal vane body (1); producing a plurality of especially stud-like raised elements (5) on an outer surface of a blade (3) of a metal vane body (1), boring impact cooling bores (8) between said raised elements (5), from the outer surface to the hollow space (4) inside the metal vane body (1), applying a coating (11) which fills the intermediate spaces (7) between the raised elements (5) and seals the impact cooling bores (8), said coating consisting of a heat-resistant, removable material, applying a cover layer (9) which adheres to the bright metallic top surfaces (6) of the raised elements (5), and removing the material in the intermediate spaces (7) between the raised elements (5) of the metal vane body (1) and the cover layer (9). The invention also relates to a gas turbine vane produced according to this method.
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