| Citation: | Long Lian, Zhang Huiliu, Wang Qinqin, et al. Influence of blowing ratio on comprehensive cooling efficiency of turbine blades with shaped film hole[J]. Journal of Aerospace Power, 2026, 41（7）：20250005 doi: 10.13224/j.cnki.jasp.20250005
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In order to investigate the influence of the geometry of the air film hole and their blowing ratio on the cooling characteristics and flow structure of the air film, a numerical study on the comprehensive cooling efficiency of the first stage turbine moving blade was conducted. A conjugate heat transfer numerical model of the turbine rotor blade was established and verified. The comprehensive cooling efficiencies of the blade with three special-shaped film holes (cylindrical, dustpan and dovetail) under different operating conditions were compared and analyzed. The mixing characteristics of film cooling at different curvature positions on the suction side were clarified. The results showed that the conjugate heat transfer numerical model adopted can well predict the distribution of the cooling efficiency on the blade surface. For the turbine blade discussed, the ideal blowing ratios for all three film- hole structures were 1.0. Under the same blowing ratio, the jet mixing range at the SS2 position was significantly larger than that at the SS1 position, and the jet mixing was more intense. Using dustpan-shaped holes on the suction side of the blade can achieve better economic benefits.
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