摘要
介绍了液氧/甲烷气液喷注器热试验情况,试验燃烧室压力7.1～7.4MPa,混合比3.5～3.9。研究了不同的喷嘴结构参数对燃烧性能和流量特性的影响。获得了燃烧效率、流量系数、振动、点火性能以及积炭特性等重要参数。
The firing tests of a LOX/CH4 subscale thrust chamber are presented in this paper. The chamber pressure of the tests is between 7.1 and 7.4MPa. The mixture ratio is between 3.5 and 3.9. Effects of design parameters on the LOX/CH4 coaxial injector combustion and discharge performance are investigated by firing tests. Some key parameters are obtained such as combustion efficiency, discharge coefficient, vibration, ignition and the soot formation characteristics. The firing tests are important base for the development of a LOX/CH4 rocket engine.
出处
《火箭推进》
CAS
2010年第4期59-62,共4页
Journal of Rocket Propulsion
关键词
液氧/甲烷
推力室
燃烧效率
同轴式喷嘴
试验
LOX/CH4
subscale thrust chamber
C＊efficiency
coaxial injector
hot fire test
