Experimental and numerical investigations were conducted to examine the influence of inlet incidence angle and squealer tip cutback on a turbine blade. The measurements of aerodynamic loss and tip heat transfer were performed under transonic conditions. Numerical models were established and validated using experimental data to gain insight into the underlying flow and thermal physics. The results demonstrate that as the incidence angle increases, the strength of TLV and UPV is significantly intensified, leading to a substantial increase in aerodynamic losses. Compared to the baseline case, a positive incidence angle of 7.5° can result in a 21.2% rise in the area-averaged TPL, while a negative incidence angle of −7.5° can reduce the area-averaged TPL by 3.2%. Moreover, the changes in incidence angle have a significant impact on the distribution of heat transfer within the tip cavity. Furthermore, a cutback squealer tip configuration was proposed and compared to a full squealer tip under a positive incidence condition. The results show that by implementing a tip cutback configuration, the leakage loss of the turbine blade can be reduced by 4.1%. Additionally, there were notable changes in tip heat transfer near the notched rim and trailing edge when employing the cutback tip.

中文翻译：

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入射角和啸声叶尖缩减对跨音速涡轮叶片气动热性能的影响

进行了实验和数值研究，以检查入口入射角和啸声器尖端缩减对涡轮叶片的影响。空气动力损失和尖端传热的测量是在跨音速条件下进行的。使用实验数据建立和验证数值模型，以深入了解潜在的流动和热物理。结果表明，随着入射角的增加，TLV和UPV的强度显着增强，导致气动损失大幅增加。与基线情况相比，7.5°的正入射角可导致面积平均TPL上升21.2%，而-7.5°的负入射角可使面积平均TPL降低3.2%。此外，入射角的变化对尖端腔内的传热分布有显着影响。此外，还提出了一种缩减型啸叫器尖端配置，并与正入射条件下的全啸叫器尖端进行了比较。结果表明，通过实施叶尖缩减配置，涡轮叶片的泄漏损失可减少4.1%。此外，当采用缩径尖端时，凹口边缘和后缘附近的尖端传热发生显着变化。