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采用数值模拟方法研究了静止和旋转涡轮叶片表面不同工况下的气膜冷却效果,计算给出了吹风比M=1.0、1.5等工况下静止和旋转叶片压力面、吸力面的气膜冷却效率,以及不同射流孔下游的气膜冷却效率,并分析了旋转和吹风比对气膜冷却效果的影响。结果表明:静止叶栅,M=1时叶片气膜冷却效果较好,旋转叶栅,M=1.5时叶片气膜冷却效果较好;叶栅在高速旋转时,冷却气流对射流孔附近区域影响不大,叶片尾缘附近气膜冷却效率呈现先增大后减小的趋势;叶片高速旋转时,产生的离心力使冷却气流流向叶顶区域,靠近叶顶区域的气膜冷却效率值较高。
The numerical simulation method was used to study the film cooling effect under static and rotating turbine blade surface conditions. The film cooling of the static and rotating blade pressure surface and suction surface under the conditions of blowing ratio M = 1.0 and 1.5 were calculated. Efficiency, and film cooling efficiency downstream of different jet holes, and analyzed the effect of rotation and blowing ratio on the film cooling effect. The results show that for the stationary cascade, the film cooling effect is better when M = 1, and the cooling effect is better when the rotating cascade is M = 1.5. When the cascade rotates at high speed, the effect of cooling airflow on the area near the jet hole The cooling efficiency of the gas film at the trailing edge of the blade first increases and then decreases; the centrifugal force generated by the rotation of the blade at high speed causes the cooling airflow to flow toward the tip region, and the film cooling efficiency value near the tip region is relatively high.