大转角反弯叶栅气膜冷却实验研究
An Experimental Study of Cooling Film in Negatively Bowed Cascade with Large Turning Angle
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摘要: 对大转折角气冷涡轮直、反弯叶栅出口流场进行了不同位置10排孔喷气及多排孔喷气等26套冷却方案测量。结果表明,无冷气喷射时反弯叶栅内损失高于直叶栅;压力面、吸力面近尾缘处喷气可降低叶栅损失;反弯叶栅前部多排孔气膜冷却的损失增加值要低于直叶栅,后部多排孔喷气则可降低叶栅损失。Abstract: Transverse measurements are carried out at the outlet of the straight and negatively bowed turbine cascades with 106° turning angle respectively with and without cooling air injection from holes of the ten rows and from holes of several rows of the ten rows (totally 26 schemes).Experimental results show that negatively bowed cascade produces more energy loss than the straight one without cooling air injection.Cooling air injection from the holes on the pressure surface and from the holes on the suction surface near the trailing edge can reduce energy losses in both the straight and the negatively bowed cascades.The increase in loss is less in negatively bowed cascade than that in the straight one with cooling air injection from holes of several rows at the leading edge,whereas cooling air injection from holes of several rows at the trailing edge reduces the energy loss in the negatively bowed cascade.
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