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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。
In order to obtain the film cooling characteristics of the single row of dustpan-shaped film holes at different positions of the turbine vane pressure surface, the cooling of the four rows of dustpan-shaped film holes in the pressure field of the turbine vane was measured in the short-period transonic heat exchanger wind tunnel respectively Efficiency at the relative arc length of 10.7%, 21.1%, 36.1% and 64.3% respectively. The cooling efficiency distributions of dustpan-shaped gas film holes under different mainstream Reynolds number, Mach number, blow ratio and hole position were obtained. The results show that the cooling efficiency decreases with the increase of Reynolds number in the holes 1 and 2 near the leading edge, while the small Reynolds number (Re = 2.0 × 105), the change of Reynolds number (Re = 4.0 × 105, 6.0 × 105) had little effect on the cooling efficiency; the ratio of the back arc length to the aperture ratio x / d = 0 ~ 40 The average cooling efficiency firstly increases and then decreases with the increase of blowing ratio. The average cooling efficiency reaches the highest when the blowing ratio is 1.0. The film cooling efficiency is higher at the hole near the trailing edge. However, as the distance increases Decline faster.