The aerothermal behavior of turbine blade tip has been studied for decades, mostly using stationary linear cascade. The blade rotation effect still remains unclear to the tip research community. This paper investigates two squealer tip cooling configurations with the effect of relative casing movement. The numerical method was validated against thermal measurement obtained in a transonic wind tunnel. Further analysis is presented for cases with relative casing motion. Dramatic changes in aerodynamics and heat transfer were observed, mostly due to the strong interactions between the over tip leakage flow and the coolant injection. The need to consider the rotating effect into future experimental validation is highlighted.

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