基于不平衡加速响应信息的柔性转子双面平衡  

Two-plane Balancing of Flexible Rotor Based on Accelerating Unbalancing Response Data

作　　者：黄金平[1] 任兴民[1] 邓旺群[2] 刘婷婷[1] 

机构地区：[1]西北工业大学振动工程研究所,陕西西安710072 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《航空学报》2010年第2期400-409,共10页Acta Aeronautica et Astronautica Sinica

基　　金：航空科技创新基金(07B08004)

摘　　要：模态平衡法和影响系数法是转子平衡中最常用的两类方法,它们都以转子的稳态响应为基础,因此称之为"稳态平衡方法"。针对当前转子稳态平衡方法中存在的不足,提出了利用不平衡加速响应信息进行柔性转子平衡的新方法。为了描述模态不平衡相对键相槽的角位置,首次引入了模态不平衡方位角的概念,并通过转子的不平衡加速响应信息对其进行了识别;在此基础上,结合转子的模态知识,添加合理的平衡试重组,利用各阶模态试重大小与对应阶模态不平衡响应幅度增量的线性关系,识别出校正质量组的大小,通过双面加重的方法实现了转子前两阶模态的平衡。仿真和实验结果表明,该瞬态平衡方法在有效降低转子不平衡振动的同时,减少了平衡过程中的起车次数。The modal balancing method and influence coefficient method are two major rotor balancing techniques commonly employed in practice. Both methods concentrate on the constant rotating speed case,i.e.,the so-called ＂steady state＂ case,so we call them steady state balancing methods. In practical application,they meet more or less difficulties. In view of this,a new balancing method based on accelerating response data is proposed here. The modal unbalance angle is presented for the first time,which represents the angular location of the modal unbalance to the key-slot,and an identification method of the angle is introduced by using accelerating response data. After that,according to the modal knowledge,a pair of appropriate trial weights is determined and placed on the rotor,and then the correction masses are calculated by using the linear relationship between the modal trial weights and the corresponding modal response increment. Thus,the first two modal imbalances are balanced by utilizing the two-plane balancing method. The simulation and experimental results show that not only the residual vibration but also the frequency of run-ups in the balancing process can be reduced effectively.

关 键 词：航空航天推进系统 转子 加速响应 动平衡 瞬态平衡 不平衡识别 

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] TB123[理学—工程力学]