305 プラズマ溶射による多孔質セラミックコーティングの遮熱性能について(OS3-2 薄膜・コーティング材の機械的特性と界面強度特性)

概要

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It is very important to apply advanced material and cooling system to gas turbine blade in order to develop the advanced gas turbine with a high-efficiency. As the state of the arts in those technologies, directionally-solidification or single crystal nickel based super alloy has been applied to the blade. Otherwise, in cooling technology, combination of film and impingement cooling systems is still utilized. In development of the advanced gas turbine, other superior cooling system is needed. The aim of this study is to develop the hybrid cooling system of ceramic porous thermal barrier coating and transpiration cooling system. This report shows the result in trial of ceramic porous thermal barrier coatings based on atmospheric plasma-spraying process that the original thermal barrier coating has been deposited. As obtained results, porous thermal barrier coating deposited with combination of composite powder of partially-stabilized zirconia and polyester powders, and low deposition speed as the spraying condition was developed. The porous coating indicated that the thermal conductivity has a half of the original coating, in spite of the almost same adhesion strength to the original one. Finally, by conducting thermal exposure test with temperature gradient field as simulating hot gas field in gas turbine, it was found that the temperature drop between hot gas temperature and coating temperature reached to 200℃.
2010-10-09