摘要
为分析主喷管角度对塞式喷管性能的影响,对两种塞式喷管实验发动机进行了热试和冷流试验。试验结果表明,主喷管倾角对发动机喷管效率、底部压强与燃烧室压强之比的影响明显,且存在一个性能最优的最佳倾角。热试和冷流实验发动机主喷管倾角为20°时,喷管效率最高。
The hot fire and cold flow experiments of two kinds of test plug nozzle engines were done to know more about the influence of plug nozzle performance by changing the angle of the primary nozzle. The experiment result was showed that the influence of nozzle performance such as the nozzle efficiency and ration of base pressure to chamber pressure was distinct while the angle of the primary nozzle was changed. There was a optimal slope angle with best performances. The nozzle efficiency was the biggest when slope angle of the test nozzle engine in the two kinds experiments was 20°.
出处
《上海航天》
2004年第2期45-49,共5页
Aerospace Shanghai
基金
国家863基金资助项目(863 2 3 4 10)
(863 2 1 3 1)
关键词
液体火箭发动机
塞式喷管
喷管性能
倾角
实验研究
Liquid rocket engine
Plug nozzle
Nozzle performance
Slope angle
Experiment study