压气机转子漏流涡与叶片气弹稳定性的相关性  

RELATIONSHIP BETWEEN BLADE FLUTTER AND LEAKAGE VORTEX OF COMPRESSOR ROTOR

作　　者：李克俭[1] 张扬军[1] 陶德平[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1995年第3期280-282,共3页Journal of Aerospace Power

基　　金：国家自然科学基金;航空科学基金

摘　　要：探讨压气机转子漏流涡与叶片气弹稳定性的相关性。将翼尖涡法（ＴＶＭ）和集中翼尖涡法（ＣＴＶＭ）分别与预估叶片颤振的变形激盘法相结合，探讨了漏流涡与叶片气弹稳定性的相关性。计算结果表明，漏流涡对叶片气弹稳定性影响较大，大涡量的漏流涡能抑制叶片颤振发生。计算结果与实验一致。By using the Tip Vortex Method (TVM) and the Center Tip Vortex Method (CTVM) with the deforming disk method of flutter prediction respectively,the relationship between the tip leakage vortex and the blade aeroelastical stability has been studied.The results show that the tip leakage flow vortex has a great effect on the blade aeroelastical stability and large tip leakage vorticity may restrain blade flutter.The calculational results are consistent with the experimental data.

关 键 词：压气机 稳定性 转子 气动力弹性 航空发动机 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程] V231.96