摘要
为提高高压液体火箭发动机上密封的工作可靠性 ,对高压密封的设计结构进行了系统的研究。根据高压密封可靠工作的条件 ,提出了新结构密封应采用自紧式设计结构的指导思想 ,并设计了多种新的密封结构。通过对比试验筛选 ,研制了 1 2种新的密封设计结构。试验证明 :新结构密封工作可靠 ,性能良好。并已在各型号的发动机上广泛地推广应用。
In order to achieve a higher reliability of high-pressure liquid rocket engine sealing structure, a systematic study on high-pressure sealing structure was conducted. In accordance with the sealing structure safe-working condition:sealing pressure ratio does not drop under the high pressure of sealing medium, it was proposed that a new sealing structure should be self-tight type.Several new sealing-structures were designed and 12 were proved to be reliable with high performance and have been used in many types of rocket engines economically.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2000年第4期16-19,共4页
Journal of Propulsion Technology
关键词
液体推进剂火箭发动机
密封
火箭发动机
Liquid propellant rocket engine
Sealing
High pressure sealing
Sealing material
Sealing test
