摘要
针对某型液体火箭发动机工艺试车后涡轮端轴密封泄漏量超标,导致发动机无法正常交付的问题,提出一种基于发动机结构和密封原理的轴系回转工艺方法,分析工艺可行性并设计制作工装,通过工艺试验获取密封性能改善的工艺参数。试验结果表明,在不分解发动机情况下,该工艺可改善发动机工艺试车后涡轮端轴密封的贴合状态,减小密封泄漏量,提升涡轮端轴密封可靠性和复用性。
Based on engine structure and sealing principles,a shaft rotation processing method is proposed to address the issue of excessive leakage of turbine end shaft seal after testing of a type of liquid rocket engine,which leads to the inability to deliver the engine normally.The feasibility of the technique is analyzed,and craft equipment is designed and manufactured to obtain process parameters for improving sealing performance by process testing.The experimental results show that after engine process testing,it can improve the fitting state of the turbine end shaft seal,reduce seal leakage,upgrade the reliability and reusability without decomposing the engine.
作者
史福俊
梁相鹏
张永强
蔡延波
庞少杰
Shi Fujun;Liang Xiangpeng;Zhang Yongqiang;Cai Yanbo;Pang Shaojie(Xi’an Space Engine Co.,Ltd.,Xi’an 710100)
出处
《航天制造技术》
2024年第1期57-60,共4页
Aerospace Manufacturing Technology
关键词
涡轮端轴密封
泄漏量
轴系回转
turbine end shaft seal
leakage amount
axis rotation
