燃气轮机叶片前缘气膜冷却的数值模拟

Numerical simulation on leading edge film cooling of gas turbine blade

采用数值模拟方法,对燃气轮机叶片前缘气膜冷却问题进行了数值模拟研究。对比分析了在不同吹风比时,叶片吸力面气膜冷却效果的变化规律以及前缘表面不同位置冷却气膜孔排的下游曲率变化对冷却效果的影响。结果表明:不同冷却排孔的冷却效果向下游呈现出逐渐减弱的趋势,每排气膜孔减弱程度各不相同;当吹风比小于1.0时,吸力面气膜冷却效果随着吹风比的增大而逐渐明显;当吹风比大于1.0时,吸力面气膜冷却效果随着吹风比的增大而逐渐减弱。

The numerical simulation method was used to simulate the leading edge film cooling of gas turbine blade. The change of film cooling effect with air blow ratio on blade suction surface and the effect of the downstream curvature of the cooling film hole row at different curvature positions on the blade leading edge surface on the film cooling effect were compared and analyzed under different blowing air ratio.Resuls showed that the cooling effect showed a downward trend in the downstream of different cooling holes, but the weakening trend in each hole of the exhaust film was different. When the blowing ratio was less than 1.0, the film cooling effect of the suction surface gradually became better as the blowing ratio increased. When the blowing ratio was greater than 1.0, the cooling effect of the suction film gradually deteriorated as the blowing ratio increased.