叶片脱落诱发的转子-盘片系统不平衡响应分析  

Analysis of Unbalanced Response of Rotor-Disk-Blades System Induced by Blade Loss

作　　者：陈雪莲[1,2] 曾劲[3] 马辉[3,4] 范晓宇 CHEN Xue-lian;ZENG Jin;MA Hui;FAN Xiao-yu(Department of Information Engineering,Liaoning Provincial College of Communications,Shenyang 110122,China;Shenyang Institute of Automation Chinese Academy of Sciences,Shenyang 110016,China;School of Mechanical Engineering&Automation,Northeastern University,Shenyang 110819,China;Key Laboratory of Vibration and Control of Aero-Propulsion Systems Ministry of Education of China,Northeastern University,Shenyang 110819,China;AECC Shenyang Liming Aero-Engine Co.,Ltd.,Shenyang 110043,China)

机构地区：[1]辽宁省交通高等专科学校信息工程系,沈阳110122 [2]中国科学院沈阳自动化研究所,沈阳110014 [3]东北大学机械工程与自动化学院,沈阳110819 [4]东北大学,航空动力装备振动及控制教育部重点实验室,沈阳110819 [5]中国航发沈阳黎明航空发动机有限责任公司,沈阳110043

出　　处：《航空发动机》2020年第4期52-57,共6页Aeroengine

基　　金：辽宁省博士科研启动基金(20170520222);国家自然科学基金(11772089);中央高校基本科研业务费专项资金(N170308028,N170306004);辽宁省高等学校创新人才支持计划(LR2017035)资助。

摘　　要：为了厘清叶片脱落诱发的失衡载荷及瞬时冲击对航空发动机转子系统动特性的影响,以转子-盘片系统为研究对象,考虑弹性支承的影响,基于ANSYS/LS-DYNA软件建立系统的有限元模型,模拟叶片脱落对转子-盘片系统振动响应的影响,分析转子转速、不平衡量、盘偏置量及支承刚度对系统不平衡振动响应的影响规律。结果表明:轴承支承总反力的变化趋势与系统不平衡量的变化趋势相同;盘片结构越靠近轴承支承端,轴承支承总反力越小;刚性支承(≥10^7N/m)下轴承支承总反力较柔性支承(<10^7N/m)下的偏大。该研究可为转子-盘片系统的结构设计提供参考。In order to clarify the influence of unbalance load and transient impact induced by blade loss on the dynamic characteristics of aeroengine rotor system,the rotor disk system was taken as the research object and the influence of elastic support was considered. The finite element model of the system was established based on ANSYS/LS-DYNA software to simulate the influence of blade loss on the vibration response of rotor-disk-blades system. The influences of rotor speed,unbalance value,disk offset value and support stiffness on the unbalanced vibration response of system were analyzed. The results show that the variation trend of the total reaction force of bearing support is the same as that of the system unbalance value. The closer the disk-blades structure is to the bearing support end,the smaller the total reaction force of the bearing support is. The total reaction force of bearing under rigid support(≥10^7 N/m) is larger than that under elastic support(<10^7 N/m). The research can provide reference for the structural design of rotor-disk-blades system.

关 键 词：叶片脱落 转子-盘片 弹性支承 有限元 航空发动机 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]