摘要
在环形叶栅低速风洞上,详细测量了具有后部加载叶型的常规直叶片和弯扭叶片栅能量损失由栅前至栅后的发展。实验结果表明损失的增长主要发生在前缘和尾缘附近,提高此类叶栅流动效率的关键是前缘圆直径、尾缘逆压段长度与逆压梯度值的匹配以及沿叶高静压系数分布规律的选择。
The experimental investigation was conducted in a low speed annular wind tunnel. The energy loss evolution from the upstream to the downstream in the blade cascade channel with aft-loaded profiles was measured in detail. The results of the present study showed that energy loss occurs mainly in the places near the leading and the trailing edges. Therefore, the measures to be taken are to choose the leading edge diameter, to match the portion of adverse pressure gradient zone with its value and to improve the static pressure distribution along span height.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2004年第1期118-125,共8页
Journal of Aerospace Power
基金
国家重点基础研究发展规划资助项目(G1999022307)
国家教委博士点基金资助项目(EDAF-24403003HB-0241)
