不同端壁间隙下压气机平面叶栅角区流动的数值模拟和实验研究  

Numerical and Experimental Investigation on Corner Flow Structure in a Planar Compressor Cascade With Different Clearances

作　　者：王子楠[1,2] 高磊[1,2] 耿少娟[1] 张宏武[1] 

机构地区：[1]中国科学院先进能源动力重点实验室(工程热物理研究所),北京100190 [2]中国科学院大学,北京100190

出　　处：《工程热物理学报》2015年第7期1428-1432,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.50906080)

摘　　要：采用数值模拟和实验方法,对比分析了不同端壁间隙下平面叶栅攻角损失特性与角区流动结构的关联。各间隙情况下,当来流攻角大于某一数值时,角区失速的发生使得叶栅总压损失呈突跃式增加。小于该来流攻角时,无间隙叶栅损失最小。大于该来流攻角时,无间隙叶栅损失最大。分析表明,间隙的存在可以抑制间隙侧角区分离,并同时推迟无间隙侧角区失速的发生。The loss characteristics and the corner flow structure in a planar compressor cascade with different clearances have been experimentally and numerically studied. For each cascade clearance size, there is a critical incidence angle for the occurrence of corner stall, which leads to a sudden increase of total pressure loss. Before this critical incidence angle, the non-clearance cascade has the lowest loss. While after that, the non-clearance cascade has the highest loss. The existence of a clearance can suppress the corner flow separation at the clearance side and postpone the corner stall at the non-clearance side.

关 键 词：压气机 平面叶栅 角区分离 泄漏流 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]