液氧/甲烷气液喷注器试验研究  

Experimental investigation on LOX/CH_4 subscale thrust chamber

作　　者：李丹琳[1] 栾叶君[1] 孙纪国 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2010年第4期59-62,共4页Journal of Rocket Propulsion

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.

关 键 词：液氧/甲烷 推力室 燃烧效率 同轴式喷嘴 试验 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]