Effects of inclined suction-side squealer and film cooling schemes on tip aerothermal characteristics for a turbine blade

Tip-leakage flow is a major contributor to both aerodynamic loss and high heat transfer on the blade tip. In this study, several rotor-tip geometries are examined numerically to assess how an internal inclined suction-side squealer tip and near-leading-edge film-cooling strategies (discrete-hole and inclined-slot cooling) influence the aerothermal behavior of tips, where a conventional squealer tip without film cooling is considered as the original configuration. Cooling effectiveness, heat transfer, and leakage flow behaviors are systematically evaluated by RNG k−ε turbulence model. It is found that combining the SS internal inclined squealer tip and inclined-slot cooling injected from the near-leading-edge cavity (SSIST_LECCS) can achieve the lowest tip heat transfer coefficient and reduce total pressure loss most by 4.47%.