压气机中间级转子叶片强迫振动响应快速分析  

Fast analysis of forced vibration response on intermediate stage compressor rotor blade

作　　者：韩乐[1,2] 王延荣[2] 魏大盛[2] 杨唯超 李迪 邹正平[1] HAN Le;WANG Yanrong;WEI Dasheng;YANG Weichao;LI Di;ZOU Zhengping(Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Commercial Aircraft Engine Company Limited,Aero Engine Corporation of China,Shanghai 200241,China)

机构地区：[1]北京航空航天大学航空发动机研究院,北京100191 [2]北京航空航天大学能源与动力工程学院,北京100191 [3]中国航发商用航空发动机有限责任公司,上海200241

出　　处：《航空动力学报》2022年第11期2636-2646,共11页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅳ-0002-0039,J2019-Ⅳ-0012-0080)。

摘　　要：以多级压气机第二级转子叶片为例,对其共振时的振动特征进行了快速分析。一方面通过进口边界条件修正对压气机模型进行减缩,并结合谐波方法提高了非定常气动力计算效率,另一方面利用系统在模态空间的频响关系和扫频技术进一步提高了求解效率,特别是当工程上亟需开展非定常气动力作用下的强迫振动响应分析时,可高效评估共振时叶片振动特征。结果表明:第二级转子叶片主要受上游静子激励,下游静子的势扰动影响有限,在共振转速附近易激起第15阶模态共振,叶片尖区有较高的振动应力,经瞬态响应分析,在给定的阻尼和工况下,所考查位置和方向的振动应力约71 MPa,利用扫频等方式评估共振时非定常气动力引起的转子叶片振动应力约为92 MPa。所形成的分析方法与流程有一定的普适性。The second stage rotor blade of multi-stage compressor was investigated to efficiently calculate the response caused by aerodynamic excitation. The compressor was reduced through the inlet boundary correction, and combined with the harmonic method to improve the calculation efficiency of unsteady aerodynamic force. The relationship between frequency and response in modal space and the harmonic analysis method were used to further improve the solution efficiency. When the forced vibration response analysis under aerodynamic excitation was urgently required in engineering, the blade vibration features at resonance can be evaluated efficiently. The results showed that the excitations of the second rotor blade was mainly subject to the upstream stator passing frequencies, and the influence of the downstream stator was limited. The 15th modal shape was excited near the resonance condition and there was significant vibration stress in the blade tip area. Under the given damping and simulated working conditions, the vibration stress was about 71 MPa in the examined position and direction obtained by the transient response analysis, and it was about 92 MPa under the resonance condition evaluated by the harmonic analysis method.

关 键 词：多级压气机 转子叶片 强迫振动响应 共振应力 快速分析 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]