液体火箭发动机涡轮泵转子的新型动平衡方法研究  

Novel dynamic balancing methods for turbopump rotor in liquid rocket engine

作　　者：李斌[1] 张贵田[1] 李锋[2] 黄金平[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]西安航天动力研究所,西安710100

出　　处：《振动与冲击》2011年第6期158-161,201,共5页Journal of Vibration and Shock

摘　　要：针对液体火箭发动机涡轮泵的运行特点,提出了利用起动过程的不平衡响应信息进行涡轮泵转子模态平衡的两种新方法。方法1将转子的前两阶模态不平衡分别等效为模态不平衡方位角和模态不平衡大小,在前两阶临界区内,通过转子的升速不平衡响应信息识别出对应阶模态不平衡方位角,然后利用各阶模态间的正交关系,添加合理的平衡试重组,通过两次升速起动过程完成转子前两阶模态的平衡;方法2引入了测点模态比的概念,在3圆平衡法的基础上,通过4次升速起动过程,完成了转子前两阶模态的平衡。最后通过模型实验对所提出的两种新型平衡方法进行了验证。Based on the operating characteristics of the liquid rocket engine turbopump,two novel modal balancing methods were presented by utilizing the run-up unbalance response data.In method I,the first two modal unbalances were expressed by the corresponding modal unbalance angles and the equivalent modal unbalance magnitudes respectively.And in each of the first two resonant regions,the modal unbalance angle was identified by using the accelerating response data.After that,taking advantage of the property of modal orthogonality,a pair of appropriate trial weights were determined,and the correction masses were calculated by using the linear relationship between the modal trial weights and the corresponding modal response increments.In method II,the concept of modal ratio among measurement points（MRMP coefficient） was introduced.Then,through 4 run-up processes,the three-circles balancing method was used to correct the first and second modal unbalances respectively.The proposed methods were validated by two model experiments.

关 键 词：液体火箭发动机 涡轮泵转子 转子动平衡 瞬态不平衡响应 

分 类 号：TH113[机械工程—机械设计及理论] V434.21[航空宇航科学与技术—航空宇航推进理论与工程]