| abstract |
Process of masking cooling holes (4) of a gas turbine component (1) with annexternal surface (6), comprising a cavity (2) and a plurality of cooling holes (4)nbefore coating the gas turbine component (1), comprising the steps of firstnapplying a mask material (5) to the cooling holes (4) so that the cooling holesnare filled at least closest to the external surface (6), whereby the mask materialn(5) contains a filler material. Then the mask material (5) within the coolingnholes (4) is thickening and the coating (8) is applied to the external surface (6)nof the component (1) and the masked cooling holes (4). In the end remainingnthickened mask material (5a) is removed from the cooling holes (4). |