压气机转子叶片颤振边界的预测方法  

Prediction method of blade flutter boundary in a compressor stage

作　　者：张小伟[1] 王延荣[1] 徐可宁[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2011年第2期392-396,共5页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB210103);北京航空航天大学博士研究生创新基金

摘　　要：通过发展的基于能量法的颤振数值预测方法得到了压气机转子叶片的颤振边界.将计算结构动力学(CSD)分析得到的叶片表面节点位移插值到耦合面的流体网格点上,并将设计的多层动网格技术应用于计算流体动力学(CFD)方法,实现叶栅振荡作用下的非定常分析,得到叶片表面的非定常气动功以及模态气动阻尼比.以某第一级压气机转子叶片为例,对比了不同振型、不同工况下的气动弹性稳定性,并最终在压气机转子特性图上给出了叶片的失速颤振边界.计算结果表明:所发展的数值预测方法可以用于分析压气机叶片的气动弹性稳定性,并通过模态气动阻尼比能够较好地给出压气机叶片的颤振边界.The blade flutter boundary in a compressor stage was obtained by the d eveloped numerical prediction method based on the energy method.The displacement s of blade surface structural nodes,obtained from the computational structural d ynamics（CSD） analysis,were transferred to fluid interface grids,and the designe d multi-layer moving grid technique was applied to computational fluid dynamics （CFD）.The unsteady analysis under the oscillating cascades was achieved to calcu late the unsteady aerodynamic work for aerodynamic modal damping ratio.For a cer tain first-stage compressor rotor,the aeroelastic stability of different operati ng conditions was investigated and compared at different blade modes.And the bla de flutter boundary has been obtained by analyzing the distribution of aerodynam ic modal damping ratio in compressor characteristic map.The results show that th e developed numerical method for aerodynamic modal damping ratio to determine th e flutter boundary is feasible to preliminarily predict the aeroelastic stabilit y of compressor blade.

关 键 词：叶片颤振 能量法 模态气动阻尼比 颤振边界 预测方法 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]