Process of masking cooling holes of a gas turbine component

Details Process of masking cooling holes of a gas turbine component Process of masking cooling holes of a gas turbine component

C - Chemistry, Metallurgy

23

C

C23C 4/00 (2006.01) C23C 14/04 (2006.01) C23C 16/04 (2006.01) F01D 5/00 (2006.01) F01D 5/28 (2006.01)

Patent

CA 2481111

Process of masking cooling holes (4) of a gas turbine component (1) with an external surface (6), comprising a cavity (2) and a plurality of cooling holes (4) before coating the gas turbine component (1), comprising the steps of first applying a mask material (5) to the cooling holes (4) so that the cooling holes are filled at least closest to the external surface (6), whereby the mask material (5) contains a filler material. Then the mask material (5) within the cooling holes (4) is thickening and the coating (8) is applied to the external surface (6) of the component (1) and the masked cooling holes (4). In the end remaining thickened mask material (5a) is removed from the cooling holes (4).

La présente invention concerne un processus de masquage de trous (4) de refroidissement d'un élément (1) de turbine à gaz pourvu d'une surface externe (6), comprenant une cavité (2) et une pluralité de trous (4) de refroidissement, avant le revêtement de cet élément (1). Ce processus consiste d'abord à appliquer un matériau de masque (5) sur les trous (4) de refroidissement de façon que ces trous soient remplis ou au moins fermés sur la surface externe (6), ce matériau de masque (5) contenant un matériau de remplissage. Puis ce matériau de masque (5) placé à l'intérieur des trous (4) de refroidissement est épaissi et le revêtement (8) est appliqué à la surface externe (6) de cet élément (1) et des trous (4) de refroidissement masqués. Finalement, le matériau de masque (5a) épaissi restant est retiré des trous de refroidissement (4).

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