| 摘要: |
| 通过分析某型号液体火箭发动机涡轮泵端面密封装配质量及泄漏原因，提出一种面向端面密封性能要求的锁紧螺母静压锁紧技术，开发出轴端螺母间歇式递增拧紧的工艺方法。采用接触非线性有限元技术和弹性相互作用理论建立了涡轮泵锁紧螺母连接的有限元模型，研究涡轮泵轴端螺母锁紧方式、拧紧力矩大小与密封性能之间的关系，根据工况载荷下涡轮泵对密封性能的要求反求装配连接拧紧力矩大小。通过对该型号涡轮泵进行工艺试验研究，解决了端面密封泄漏量超差问题，端面密封一次装配成功率由原来的50%提高到90%，验证了该技术方法的可行性。 |
| 关键词: 涡轮泵 端面密封 泄漏量 有限元分析 |
| 基金项目: |
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| Research on Assembly Process for Turbopump End-face Seal Performance Requirements |
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Wei Fangsheng Zou Xudong Li Bo
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(Xi’an Space Engine Co., Ltd., Xi’an 710100)
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| Abstract: |
| Static pressure locking technology is proposed based on the analysis of assembly quality and leakage of the turbopump end-face seal of a liquid rocket engine, and an intermittent tightening process for the shaft end face nut is developed. The effect of locking method and magnitude of tightening torque on the sealing performance of the turbopump locking nut are investigated with nonlinear contact finite element and elastic interaction theory. Then the magnitude of the tightening torque of the locking nut is determined according to the requirements of the turbopump’s sealing performance under variable load conditions. The leakage of the end-face seal of the turbopump is solved and the success rate of the end-face seal assembly has been increased from 50% to 90%, which indicates the feasibility of the proposed process. |
| Key words: turbopump end-face seal leakage rate finite element analysis |
