| 简介 |
The present invention relates to a process for the preparation of a ceramic thermal barrier coating (10) on a component, in particular a component of a gas turbine or of an aircraft engine or high temperature-loadedhot gas-loaded, the method comprising the steps of : a) applying a slip regions of the component surface to which the bonding layer, wherein the slip rare earth oxide particlezirconium oxide particle and/or hollow-spherical (12) contains and b) sintering the slip thus forming the thermal barrier coating (10), in such a way that the hollow-spherical embodiment of the predominantly rare earth oxide particlezirconium oxide particle and/or is maintained. The invention concerns further a thermal insulation layer (10) for components for use in compressor and turbine components, in particular for a component of a gas turbine or of an aircraft engine or high temperature-burdeninghot gas-burdening, wherein the thermal barrier coating (10) consists of a ceramic material and is sintered rare earth oxide particlezirconium oxide particle and/or as well as hollow-spherical (12) contains. Also the invention comprises a component with the novel thermal barrier coating (10). |
客服热线：
手机版
二维码
