静叶尾迹对压气机动叶非定常气动载荷的影响

Effects of Stator Blade Wakes on Unsteady Aerodynamic Loads of Compressor Rotor Blade

以某型航空发动机压气机转子系统为研究对象,建立了单级叶盘的三维结构及流场模型。通过对滑移网格(sliding mesh,简称SM)方法与运动坐标系(moving reference frame,简称MRF)方法在计算耗时和收敛性方面的比较,证明了运动坐标系方法的准确性和高效性。考虑前一级静叶尾迹的影响,求解压气机内部在不同时刻的流动特性,得到静叶尾迹对动叶流场的非定常干扰情况。经过对压气机叶顶和轮毂、动叶压力面和吸力面非定常气动载荷的分析发现:在动叶流场的前缘形成了较主流区压力和速度较低的不均匀流场,且在动叶前缘叶顶位置受到的气动载荷最为显著;动叶压力面和吸力面气动载荷的分布规律相反,从叶顶至轮毂、前缘至尾缘,压力面非定常气动载荷的大小和波动幅度逐步递减,而吸力面却与其相反,呈现出逐步递增的趋势。该研究为某型航空发动机压气机叶盘转子系统的动力学设计提供了理论依据。

This paper establishes a three-dimensional structural and flow field model of the single-stage blade-disc of an aero-engine compressor rotor system.The moving reference frame(MRF)method was proven to be more accurate and efficient than the moving mesh(MM)method in terms of time-consuming and convergence.The interference of the unsteady wakes caused by the stator rotor was obtained from inner-compressor flow characteristics considering the effects of forward stator blade wakes.Analysis of unsteady aerodynamic loads of compressor shroud and hub,rotor blade pressure and suction surface demonstrates the following:an uneven flow field was found at the leading edge of the rotor blade,whose pressure and speed was lower than that at the mainstream zone,and aerodynamic loads were the most significant at the rotor leading edge and tip;the distribution of aerodynamic loads at rotor blade pressure and suction surface was the opposite,for unsteady aerodynamic loads of pressure surface,magnitude and fluctuation amplitude gradually decreased,but showed a gradual increasing trend at the suction surface.This research provides a theoretical basis for the dynamics design of the aero engine compressor blade-disc-rotor system.