Abstract

Abstract The application of thermal barrier coatings is increasing in aeroengines. The service life of turbine components could be improved by optimized structures of the zirconia top coating. The thermal barrier coatings on turbine blades were tested in a hot gas thermal shock test. Up to 6500 thermal cycles until first spallation a plasma sprayed ceramic thermal barrier coatings can be very well compared with the service life of EB-PVD thermal barrier coatings with 8000 - 9000 thermal cycles until first spallation. Paper text in German.

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