摘要
基于能量法原理,采用弱耦合的方法对跨声速风扇叶片进行气弹稳定性分析;采用3维线性插值算法编程实现CSD/CFD数据交换。利用有限元法计算叶片的模态振型和固有振动频率;应用FLUENT动网格技术,对NASA R 67风扇叶片在不同模态振动下的非定常流场进行数值模拟,给出在前3阶模态振动下叶片表面的周期累积气动功和气动阻尼,并探讨了激波对跨声速风扇叶片气弹稳定性的影响。
Based on energy method,the aeroelastic stability of transonic fan blade was analyzed by weak coupling method.The data exchange of CSD/CFD was achieved by the 3D linear interpolation method.The mode shape and natural frequency of the blade was calculated by the Finite Element（FE） method.The numerical simulation of the unsteady flow field for NASA R67 fan blade in the different vibration modes was conducted by the FLUENT dynamic mesh technology.The cycle accumulated aerodynamic work and aerodynamic damping of blade surfaces at the first three vibration mode was obtained.The effect of shock wave on the aeroelastic stability of transonic fan blade was discussed.
出处
《航空发动机》
2011年第3期41-46,共6页
Aeroengine
