摘要
为了提高某型号液体火箭发动机涡轮泵端面密封脱开压力值的准确可靠性,提出一种基于弹力测试值理论计算脱开压力的方法,并研究出集充放气、气压检测、数据采集全过程一体化的脱开试验控制技术,采用自动化脱开试验系统对理论计算结果进行了试验验证,计算及试验结果表明,该理论计算方法及自动化脱开试验技术精确可行,提高了端面密封试验数据的稳定性和可靠性,能够有效保证液体火箭发动机的工作性能与寿命。
A method for calculating release pressure based on elastic test value theory is proposed, in order to improve the accuracy and reliability of pressure value for the turbopump face seal of a liquid rocket engine. The control technology of detachment test which integrates the whole process of gas collection, gas pressure detection and data acquisition has been developed. The experimental verification of theoretical calculation results is carried out by using automatic detachment test system. The calculation and test results show that the theoretical calculation method and the automatic detachment test technology are accurate and feasible, which can improve the stability and reliability of the test data of the end seal and effectively guarantee the working performance and life of the liquid rocket engine.
作者
魏芳胜
解庆
戚鹏举
董飞
王力
Wei Fangsheng;Xie Qing;Qi Pengju;Dong Fei;Wang Li(Xi’an Space Engine Co., Ltd., Xi’an 710100;Xi’an Aerospace Propulsion Institute, Xi’an 710100)
出处
《航天制造技术》
2019年第4期27-30,共4页
Aerospace Manufacturing Technology
