| Citation: | Luo Jianxia, Chen Dawei, Tan Zhiyong. Optimization and improvement of the cooling scheme for high pressure turbine blade[J]. Journal of Aerospace Power, 2026, 41（8）：20240781 doi: 10.13224/j.cnki.jasp.20240781
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To enhance the cooling effect, an optimized cooling scheme for the rotor blade was developed, and overall cooling effectiveness of the blade was verified. For the prototype blade, elevated temperatures were observed at the leading edge, the trailing edge, and the mid-region of the suction side.. As the flow ratio increased to 5% and 7%, the film cooling effectiveness deteriorated on both the pressure and suction sides. This degradation led to a corresponding temperature rise at the measured points. The optimized blade design achieved a more uniform blade temperature distribution and enhanced overall cooling efficiency through optimization of the internal cavity and film hole design. At the same flow ratio, temperatures at the measurement points in the front regions of the pressure and suction sides dropped by about 30K compared to the prototype design, with an improvement of 0.02 in overall cooling effectiveness. As the flow ration increased, the optimized design consistently provided good film coverage, leading to a continuous decrease in blade measurement point temperatures with the overall cooling effectiveness increasing from 0.568 to 0.613.
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