转子突加不平衡响应试验及数值研究  

Test and Numerical Research for Sudden Unbalance Response

作　　者：罗灵 宣海军[1,2] 

机构地区：[1]浙江大学能源工程学院高速旋转机械实验室,杭州310027 [2]先进航空发动机协同创新中心,北京100083

出　　处：《机械工程师》2017年第11期86-89,共4页Mechanical Engineer

基　　金：航空推进技术验证计划资助(APXX)

摘　　要：叶片飞脱引起的转子不平衡瞬态响应是备受关注的重要问题之一。为研究某小型发动机叶片飞脱后的不平衡响应,在高速旋转试验台上进行叶片飞脱试验,测量转子的位移数据,并用高速相机记录叶片飞脱过程。运用传递矩阵法建立了单盘双支承转子系统的运动方程,用Newmark-β法积分求解,模拟了转子在双叶片顺序飞脱下的不平衡响应。试验和计算结果表明,叶片飞脱后的转子振动存在剧烈振荡、慢速涡动和平稳振动三个阶段。Transient unbalance response due to blade released is a more concerned problem. Aiming at studying unbalance response of small aero-engine, the blade-out test is conducted on the high speed spin tester. Displacement and photographes of blade-out are also recorded. The transient motion of single disc and two bearing is established on Transfer Matrix Method （TMM）. The unbalance response of two-blade out are simulated by Newmark-β integration method. The results show that vibration can be divided into three stages, which are severe stage, slow whirl stage and steady stage.

关 键 词：不平衡响应 试验 传递矩阵法 双叶片飞脱 慢速涡动 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]