低展弦比涡轮静叶栅叶片正弯曲作用的试验研究  

EXPERIMENTAL INVESTIGATION ON THE EFFECTS OF POSITIVE BLADE BOWING IN TURBINE STATOR CASCADES WITH LOW ASPECT RATIO

作　　者：陈海生[1] 谭春青[2] Yamamoto Atsumasa 梁锡智[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国科学院工程热物理研究所,北京100080 [3]日本航空宇宙技术研究所

出　　处：《机械工程学报》2005年第2期65-70,76,共7页Journal of Mechanical Engineering

摘　　要：对弯曲叶片研究中代表性的HIT涡轮静叶型重新开展了叶片弯曲对低展弦比涡轮静叶栅流场影响的试验研 究。测量了直叶片叶栅、+10°、+20°和+30°弯曲叶片叶栅的进、出口流场,分析了叶片弯曲对叶栅出口二次流、 总压损失和气流角的影响。结果表明:对该叶型叶栅,叶片正弯曲既不能大幅度降低叶栅二次流损失,也不能改 善叶栅出口气流角沿叶高的分布:叶栅出口二次流动、尾缘涡及壁角涡随叶片正弯曲角的增大而增强,而通道涡 强度和位置变化不大;该研究结果同以往有关文献的研究结果完全不同。Experimental investigation on the effects of positive blade bowing on the flow fields of turbine stator cascades with a typical blade profile (HIT profile) and low aspect ratio are re-carried out. The flow fields at inlet and outlet of cascades with straight blades and +10? +20? +30?bowed blades are measured, and the effects of blade positive bowing on secon dary flow, total pressure loss and outlet flow angle are analyzed quantitatively. The results show that, for the present blade profile, the positive blade bowing can neither decrease the secondary flow losses nor improve the distribution of exit flow angles, intensity of the secondary flow, tail vortex and corner vortex are all increased with the increasing of bowing angle while the intensity and position of passage vortex do not change obviously. The conclusion of present experiments is different from the comparative references.

关 键 词：涡轮 静叶栅 弯曲叶片 试验 流场 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]