摘要
利用自主开发的三维流场求解器MFlow,基于混合平面法技术对航空发动机压气机流场进行了数值模拟。在转/静子交界面处的不同的展向位置,将流动周向平均后进行传递,使得非定常流动问题简化成为"准定常"问题,从而将计算过程简化为只需要对一个叶片流道进行计算,大大减小了计算量。通过计算得到了压气机的总体工作特性和几个关键气动参数的展向分布曲线,并将结果与试验数据进行了对比分析。计算结果和试验数据基本吻合,验证了计算程序的适用性和可靠性。
An in-house three-dimensional unstructured-grid flow solver based on a mixing plane method was used to simulate the flow field of the compressors.Pitchwise averaging was used at the rotor/stator interface for information transport,making the unsteady problem to be-come a “qusi-steady”one.Thereafter the computational gird needs only one flow passage,which greatly reduced the amount of the calculation.Two different transonic compressors,NASA rotor 67 and stage 35,were tested in this paper.The overall performance maps and spanwise profiles of several aerodyamic parameters were obtained from the calculation,and the results were com-pared to the experiment data.The results presented here including pressure ratio,temperature ratio and adiabatic efficiency are in good agreement with the experiment data,indicating the ap-plicability and reliability of the method.
出处
《空气动力学学报》
CSCD
北大核心
2015年第5期631-635,共5页
Acta Aerodynamica Sinica
关键词
压气机
数值模拟
混合平面法
气动性能
turbomachine
numerical simulation
mixing plane
aerodynamic performance
