不同周向位置端壁翼刀对压气机叶栅损失影响的实验研究  

Experimental Investigation of the Affect of Endwall Fence Location on Compressor Cascade Loss

作　　者：田夫[1] 钟兢军[1] 孟丽艳[2] 

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 [2]北京师范大学信息科学与技术学院,北京100875

出　　处：《航空动力学报》2005年第4期613-618,共6页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50076009);全国优秀博士学位论文作者专项基金资助(199932)

摘　　要：在低速大尺寸叶栅风洞上通过详细测量叶栅流场,研究了叶栅端壁上不同周向位置处加装端壁翼刀对压气机叶栅损失和二次流的影响。实验结果表明,合理选择翼刀安装位置,可有效地控制压气机叶栅的二次流,降低叶栅的总损失。进一步对实验方案中叶栅总损失最小的翼刀位置的叶栅内流场进行了测量,分析了安装翼刀后流场内涡系结构的变化,探讨了翼刀涡的形成和发展变化。The affect of endwall fences at different locations on compressor cascade loss and secondary flow were investigated through detailed experimental investigation in a low speed wind tunnel. The results show that the secondary flow in the compressor cascade can be controlled effectively and the total cascade loss can be reduced in case of the proper selection of the end wall fence location. Through the measurement of the cascade internal flow with the optimum fence location in terms of minimum loss,the vortices in the cascade with endwall fence were analyzed. The formation and development of the endwall fence vortices were also discussed.

关 键 词：航空 航天推进系统 压气机叶栅 端壁翼刀 周向位置 二次流 叶栅损失 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]