Abstract: A GH 2/LO 2/RP 1 injector is an important component of tripropellant rocket engine. Four types of tripropellant injectors were employed to present the atomization characteristics test. The regularities of the injectors’ atomization characteristics variation with each propellant injection pressure drop were studied,the effects of the injectors’ configuration on the atomization performance were analyzed,the atomization performance of single injector was compared with those of three injectors at the same operating conditions,the atomization characteristics tests of the tripropellant operating conditions and the bipropellant operating conditions were presented . The tests results show that the atomization performance of the swirl coaxial injector with premixed fuel injection is the best . The conclusions obtained in this paper provide an important reference for the optimization design of tripropellant injectors and gas/liquid coaxial injectors.

Key words: Liquid propellant rocket engine;Tripropellant;Injector;Propellant spray;Cold flow

摘要： 三组元喷嘴是气氢／液氧／煤油火箭发动机的重要部件，对４ 种类型的三组元喷嘴进行了雾化特性试验， 研究了喷嘴的雾化特性随各组元喷注压降的变化规律， 分析了喷嘴结构对雾化性能的影响， 比较了相同工况下单喷嘴和三喷嘴的雾化性能， 进行了三组元工况和双组元工况下的雾化特性试验， 试验结果表明同轴离心内混式喷嘴的雾化性能较好。所得结论对三组元喷嘴和气液同轴式喷嘴的优化设计有重要的参考价值

关键词: 液体推进剂火箭发动机;三元推进剂;喷嘴;推进剂雾化;冷流