摘要
使用数值计算的方法对某型压气级静叶栅的直叶片与弯叶片变攻角特性进行了对比研究,结果发现弯叶片对正攻角下的流场特性有明显的影响。由于端区扩压因子的减小和近端区吸力面一侧的密流的增加,所以弯叶片能够消除或推迟在大正攻角下近吸力面角区分离的产生。弯叶片也因此可以扩大叶栅稳定工况范围,分析结果表明在某一弯角(20°)时,达到最大,临界攻角为16°。
The effects of the compressor bowed stator vanes on variable incidence characteristics were studied with the method of CFD. It was found that bowed vane had strong impact on flow field under positive incidence. Due to the decrease of diffusion factor near the end-wall and the augmentation of density mass flow close to the suction surface, the bowed blade eliminates or defers the separation formation near suction surface under high positive incidence and weakens the expanding of the separation region. There fore, bowed blade is able to enlarge the operation range of the stator vane. The results show the bowed blade with bow angle of 20° has maximal operation range with critical incidence of 16°.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期396-402,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助(50236020)
关键词
航空
航天推进系统
低速
攻角
压气机静叶
弯叶片
临界攻角
数值分析
aerospace propulsion system
low mach number
incidence
compressor stator
bowed vane
critical incidence
numerical analysis
