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Producing a ceramic heat insulation layer on a high-temperature loaded or hot gas-loaded component o

2025-07-27 03:073770下载
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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).


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