Abstract
The aim to increase efficiency of aeroengines led to the demand for increasing combustion chamber temperatures, which can best be realized by protection of turbine blades with thermal barrier coatings (TBC). Nowadays application of TBCs in stationary gas turbines has also become of interest, although conditions concerning application temperature and lifetime are different from aeroengines. Graded alumina/zirconia thermal barrier coatings (TBCs) offer a great potential to extendthe application on aeroengine turbine blades integrating low oxygen diffusion layers of alumina. Since the thermal conductivity of alumina is higher than that of zirconia the design of the TBCs for the use in stationary temperature gradients has to be extended to same heatflux coating thickness. As a basis a processing route for alumina ingots was developed. Evaporation of alumina was carried out characterizing phase content and morphology. Co-evaporation of alumina/zirconia was used to fabricate lateral graded TBCs.
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