提高跨声速风扇转子气动负荷系数途径  

Way of Improving Aerodynamic Load Coefficient of Transonic Axial Fan Rotor

作　　者：宋西镇[1] 周盛[1] 李秋实[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100191

出　　处：《航空学报》2009年第1期12-20,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(10577002)

摘　　要：回顾了跨声速风扇/压气机转子气动负荷的研究历程,并对基准风扇转子和两个方案转子进行了三维流场分析。通过对195个研究方案的对比研究,目前阶段数值模拟的结果中风扇转子气动负荷系数达到0.65。在来流条件相同的情况下:合理组织激波结构可以大幅提高叶尖气动负荷;叶根大转角设计是提高根区气动负荷的可行途径;静子跨声速来流是高气动负荷跨声速风扇/压气机的必然结果。The process of investigation into transonic fan/compressor rotors aerodynamic load is reviewed,and the 3D flow field of the baseline rotor and two new rotor projects are researched.The aerodynamic load coefficient of transonic fan rotor has reached 0.65,as obtained through comparison research on 195 projects which aim at improving the transonic fan rotor aerodynamic load.The results show that in the same inlet flow condition,higher aerodynamic load near shroud can be achieved by organizing the shock wave,high-turning angle near hub is a feasible approach to the increase of aerodynamic load,and the transonic stator is the inevitable outcome of improving the aerodynamic load of transonic fan/compressor rotors.

关 键 词：跨声速流 风扇 压气机 转子 气动负荷 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]