低速条件下压气机静叶栅中弯叶片对变攻角性能影响的数值分析  

Numerical Investigation of the Effects of Bowed Compressor Stator Vanes on Variable Incidence Performance at Low Speed

作　　者：张永军[1] 陈浮[1] 冯国泰[1] 苏杰先[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空动力学报》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)

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°.

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 

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]