Abstract: A numerical model was presented for the prediction of the unsteady aerodynamic loads on the compressor rotor to inlet distortion.Field equations for the first order unsteady perturbation were obtained by linearizing the time dependent flow conservation equations about a uniform mean steady flow.The model was used to analysis the unsteady aerodynamic loads on the first rotor of a turbojet with a distorted inflow.The numerical results show that the distribution of unsteady loads in chord is different for different radius,and the unsteady loads on the tip is largest.

Key words: Unsteady aerodynamics;Excitation force;Flow distortion;Numerical simulation;Axial flow compressor;Gas turbine engine

摘要： 为了分析畸变进气在轴流压气机转子叶片表面产生的非定常激振力 ,采用二维无粘线化非定常流理论 ,建立了周期性气流条件下叶片表面非定常气动力的计算模型 ,根据实测的畸变实验数据 ,对某发动机的第一级叶片表面非定常激振力进行了计算分析 ,结果表明在叶片的不同径向位置 ,非定常压力的分布规律不完全相似 ,而作用在叶片表面总的非定常气动力在叶尖部位最强。

关键词: 非定常空气动力学;激振力;流场畸变;数值仿真;轴流式压缩机;燃气涡轮发动机