Patent ID: 9139896
Filing Date: 2015-09-22
Classification: C23C,Y10T

Abstract:
1. A heat-insulating protective layer for a component which is to be located within a hot-gas section of a gas turbine, comprising: a bonding layer having a Ni, Co, Cr, Al, Y-containing metal alloy, wherein the Ni, Co, Cr, Al, Y-containing metal alloy is MCrAIY, where M=Ni, Co, to which one or more chemical-metal elements with a large atomic diameter selected from the group consisting of Re, W, Si, Hf and Ta are added as alloys such that the bonding layer applied to a high temperature-resistant base metal of the component has a chemical composition in accordance with: Co 15-30 wt. %, Cr 15-25 wt. %, Al 6-13 wt. %, Y 0.2-0.7 wt. %, Re up to 5 wt. %, W up to 5 wt. %, Si up to 3%, Hf up to 3 wt. %, Ta up to 5 wt. %, with a remainder consisting of Ni; a diffusion layer; and a ceramic layer, the diffusion layer arranged between the ceramic layer and the bonding layer; wherein the bonding layer, diffusion layer and ceramic layer are applied to the high temperature-resistant base metal of the component; wherein the diffusion layer is produced by alitization of the bonding layer in that a surface of the bonding layer on the base metal is alitized to form a surface-alitized MCrAlY layer that has a structure consisting of an inner, extensively intact γ, β-mixed phase, the diffusion layer consisting of an inner diffusion zone with an Al content of about 20%, and an outer built-up layer consisting of a β-NiAl phase with an Al content of about 30 wt. %, the outer built-up layer being removed essentially down to the inner diffusion zone of the diffusion layer by an abrasive treatment such that a surface of the diffusion layer has an Al content of more than 18 wt. % and less than 30 wt. %.