压气机叶栅前缘边条技术的参数化数值研究  

Parametric Numerical Study on Leading Edge Strake Blade Technique for Compressor

作　　者：唐方明[1] 伊卫林[2] 陈志民[2] 季路成[2] 

机构地区：[1]中国航空动力机械研究所,湖南株洲412002 [2]北京理工大学宇航学院,北京100081

出　　处：《航空发动机》2015年第3期66-71,共6页Aeroengine

基　　金：国家自然科学基金(51006100;51176012)资助

摘　　要：压气机来流普遍存在端区附面层扭曲问题,前期研究证实可采用叶片端区前缘边条(Leading Edge Strake Blade,LESB)技术解决,因此,进一步进行前缘边条几何影响和变工况适应性的参数化数值研究。选用折转角为60°的NACA65叶栅为例,对前缘边条高度、前伸长度以及在-5°、0°、+5°攻角下的性能进行了参数化研究,对其规律、机理进行了总结和分析。结果表明:前缘边条高度、前伸长度选取存在最佳值,边条高度选取略大于来流扭曲附面层厚度为宜,而边条长度在不同工况下好坏影响各异,需折衷考虑;所设计较优方案揭示了前缘边条对端区流动的调控作用,表现出良好的变工况性能。Inflow boundary layer skew has an universal phenomena in compressors.The previous research had proved that the Leading Edge Strake Blade （LESB） technology could resolve the problem effectively.This paper presents parametric numerical study to investigate the effect of its geometric parameters and its performance at different operating conditions.The NACA 65 compressor cascade with turning angle of 60° was chosen as a test case.Performance comparisons were performed between the original blade and LESB at incidence angle of 0°,-5° and ＋5° with simultaneously varying the length and the height of the strake.The rules and mechanisms of its effects were summarized and analyzed.The results show that there are optimum values for the length and the height of the strake.And the strake height that is slightly higher than the thickness of skewed inflow boundary layer is a suitable choice.However,the strake length needs to be compromised because of the uncertainty of the performance in different conditions.The present study reveals the regulation mechanism of LESB on the flow in end wall region,and LESB could promote compressor performance in a wide operating range.

关 键 词：前缘边条叶片 压气机 角区分离 端区流动 参数化数值研究 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]