液体火箭发动机涡轮泵转子的新型动平衡方法研究

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振动与冲击 ›› 2011, Vol. 30 ›› Issue (6) : 158-161.

论文

液体火箭发动机涡轮泵转子的新型动平衡方法研究

李斌1;张贵田1;李锋2;黄金平2

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RESEARCH ON THE NOVEL DYNAMIC BALANCING METHODSOF THE LIQUID ROCKET ENGINE TURBOPUMP ROTOR

LI Bin1;ZHANG Gui-tian1;LI Feng2;HUANG Jin-ping2

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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

Abstract

Based on the operating characteristics of the liquid rocket engine turbopump, two novel modal balancing methods have been presented by utilizing the run-up unbalance response data. In method I, the first two modal unbalance is expressed with the corresponding modal unbalance angle and the equivalent modal unbalance magnitudes respectively. And in each of the first two resonant regions, the modal unbalance angle can be identified by using the accelerating response data. After that, according to the modal knowledge, a pair of appropriate trial weights are determined and placed on the rotor, and the correction masses are calculated by using the linear relationship between the modal trial weights and the corresponding modal response increment. In method II, the modal ratio among measurement points(MRMP coefficient) is firstly introduced. Then, through 4 run-up processes, the three-circle balancing method is used to correct the first and second modal unbalances respectively. The proposed methods are validated by two model experiments

导出引用

李斌;张贵田;李锋;黄金平. 液体火箭发动机涡轮泵转子的新型动平衡方法研究[J]. 振动与冲击, 2011, 30(6): 158-161

LI Bin;ZHANG Gui-tian;LI Feng;HUANG Jin-ping. RESEARCH ON THE NOVEL DYNAMIC BALANCING METHODSOF THE LIQUID ROCKET ENGINE TURBOPUMP ROTOR[J]. Journal of Vibration and Shock, 2011, 30(6): 158-161