某级压气机叶盘系统失谐振动关键因素研究  

Study on key factors of mistuned vibration for blade-disk system of some-stage compressor

作　　者：李宏新[1,2] 袁惠群[3] 张连祥 

机构地区：[1]中国航空发动机集团有限公司沈阳发动机研究所,沈阳110015 [2]北京航空航天大学能源与动力工程学院,北京100191 [3]东北大学理学院,沈阳110004

出　　处：《航空动力学报》2017年第5期1082-1090,共9页Journal of Aerospace Power

摘　　要：基于某级压气机叶片盘扇区,建立考虑非线性榫接触叶片盘有限元模型,应用提出的自由界面子结构-固定界面预应力模态综合超单元近似分析方法,并基于提出的围绕实验与有限元分析拟合出线性表达式的失谐参数识别方法,探究失谐关键因素对于叶盘系统振动的影响.结果表明,非线性榫接触不可忽略,提出的超单元法精度达到3.07%,满足要求.同时也表明,叶片平均频率、叶盘刚度比与频率转向对于失谐叶盘系统振动幅值、共振频率及应变能等参数均有一定影响.Based on the blade disk basic sector of certain stage compressor,blade disk finite element model considering non-linear tenon contact was established,free-interface substructure-fixed interface prestressed modal synthesis super element approximate analysis method was proposed,meanwhile,mistuned parameters recognition method of linear expression was fitted based on the blade static-frequency test and dichotomy combined with finite element analysis,exploring the effects of mistuning key factors on blade disk vibration.Results show that the non-linear tenon contact cannot be neglected,and the accuracy of super element method is 3.07%,so the proposed method meets the requirement.In addition,blades mean frequency,disk stiffness ratio and frequency veering have an effect on mistuned bladed disks vibration amplitude,resonance frequency and strain energy and other parameters.

关 键 词：失谐 子结构模态综合法 非线性接触 平均频率 刚度比 频率转向 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]