Influence of turbine blade geometry on thickness of TBCs deposited by VPA and PS-PVD methods

Purpose: The authors presented in the article the influence of the jet engine turbine blade profile on the thickness and microstructure of thermal barrier coatings. Design/methodology/approach: The assessment of model blade made of ZS6K alloy used in the first stage of the turbine engine was performed. The diffusion aluminide coating as well as the thermal barrier coating were deposited on the blade surface with a use of the out of pack method. The zirconia stabilized by yttrium oxide coating was deposited by PS-PVD method The research was performed with a use of light- and scanning microscopy. Findings: It has been proven, that the thickest coating was found on the leading edge and trailing edge of the blade. In those places the coating thickness was approx. 20-30% larger than in the other areas on turbine blade. Research limitations/implications: The research was performed with a use of light- and scanning microscopy. Practical implications: The obtained results indicate that it is possible to create the thermal barrier coating by PS-PVD process on the first stage turbine blades of the aircraft engine. It indicates the possibility of application of this process in the industrial practice. Originality/value: The new method for TBC coating production were used.