摘要
针对叶片故障的原因颤振问题,基于计算流体动力学/计算结构力学(CFD/CSD)耦合算法,研究了压气机典型叶片的流固耦合(FSI)问题及颤振特性.使用有限体积法求解非定常三维Navier-Stokes方程和有限元法求解三维结构体模型,在两个求解器间由载荷转换、网格变形传递和同步化方法完成数据交换及求解.以高性能风扇NASA(National Aeronautics and Space Administration)Rotor 67为例,对其工况下的气弹响应进行分析,计算结果与实验数据进行对比,以确认方法的正确性和有效性.结果表明可根据循环功和平均压力分布来分析叶片的颤振机理,从而为压气机稳定性的判定提供重要依据.
For the most important flutter problem of turbomachinery blades,the fluid-structure interaction（FSI） problems and flutter characteristic of turbomachinery blades were studied in present paper based on the CFD/CSD（computational fluid dynamics/computational structural dynamics） algorithm.The three-dimensional unsteady Navier-Stokes equations and three-dimensional structural model were solved by the finite volume method and the finite element method,respectively.High accuracy in calculation and data exchange were gained by using load transfer,deformation tracking and synchronization between two solvers.The procedure successfully simulated the aeroelastic responses of a high performance fan rotor,NASA（National Aeronautics and Space Administration） Rotor 67,under a range of operational conditions,and the results were compared with the experiment.The results show that the flutter mechanics of the compressor blade could be illustrated based on the distribution of cycle work and mean pressure,which is helpful to the decision of compressor stability
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第5期1077-1084,共8页
Journal of Aerospace Power
关键词
流固耦合
颤振特性
非定常
气弹响应
压气机稳定性
fluid-structure interaction （FSI）
flutter characteristic
unsteady
aeroelastic responses
compressor stability
