涡轮导叶压力面簸箕形气膜孔冷却特性实验研究

发布时间：2018-03-25 03:12

本文选题：簸箕形孔　切入点：气膜冷却　出处：《推进技术》2016年12期

【摘要】：为了获得涡轮导叶压力面不同位置处单排簸箕形气膜孔的气膜冷却特性,在短周期跨声速换热风洞中分别测量了涡轮导叶压力面4排簸箕形气膜孔的冷却效率,分别位于10.7%,21.1%,36.1%,64.3%相对弧长位置处,获得了不同主流雷诺数、马赫数、吹风比和孔位下簸箕形气膜孔冷却效率的分布。结果表明:在靠近前缘的孔1和孔2处,气膜冷却效率随着雷诺数的增大而减小,而在靠近尾缘的孔3和孔4处,小雷诺数(Re=2.0×105)下冷却效率最小,中高雷诺数(Re=4.0×105,6.0×105)的变化对冷却效率影响较小;各个孔位孔后弧长与孔径比x/d=0~40区域的平均冷却效率随着吹风比的增大而先升高后降低,在吹风比为1.0时平均冷却效率达到最高;靠近尾缘的孔位处气膜冷却效率更高,但随着距离的增大下降得也更快。
[Abstract]:In order to obtain the film cooling characteristics of turbine blade pressure surface at different positions of single row dustpan shaped film holes, in the short period of transonic air hole were measured for the cooling efficiency of the turbine blade pressure surface 4 row dustpan shaped holes, respectively at 10.7%, 21.1%, 36.1%, 64.3% relative position of arc length and receive different mainstream Reynolds number, Maher number, blowing ratio and distribution of holes under the dustpan shaped film cooling efficiency. The results showed that: in the near the front edge of the hole 1 and hole 2, film cooling efficiency decreases with the increase of Reynolds number, and near the trailing edge of the hole 3 and hole 4 at small Reynolds number (Re=2.0 * 105) under the minimum cooling efficiency, high Reynolds number (Re=4.0 * 105,6.0 * 105) has little effect on the cooling efficiency of the change; each hole hole after the arc length and the aperture ratio of average cooling efficiency of x/d=0~40 region with the increase of blowing ratio increased first and then decreased, in the blowing ratio The average cooling efficiency reaches the highest at 1, and the film cooling efficiency is higher at the hole near the tail edge, but it decreases faster with the increase of distance.

【作者单位】：西北工业大学动力与能源学院;中航商用航空发动机有限责任公司;
【基金】：国家重点基础研究发展规划资助项目(2013CB035702)
【分类号】：V231.1

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