三组元喷嘴流量特性的试验研究  

Experimental Investigation on Flowrate Characteristics of Tripropellant Injectors

作　　者：沈赤兵[1] 童荣瑜 周进[1] 王振国[1] 

机构地区：[1]国防科技大学

出　　处：《中国空间科学技术》1999年第3期39-45,共7页Chinese Space Science and Technology

摘　　要：对气氢／液氧／煤油火箭发动机重要部件三组元喷嘴的四种类型进行了流量特性试验；研究了喷嘴流量随各组元喷注压降的变化规律；分析了喷嘴结构对流量系数的影响；比较了三组元工况和双组元工况下喷嘴的流量特性；测量了离心内混式喷嘴燃料内混腔中的压力并分析了该喷嘴的流量特性。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。A GH 2/LO 2/RP-1 injector is an important component of a tripropellant rocket engine.Four types of tripropellant injector were employed to conduct the flowrate characteristics test.The regularities of the injectors' mass flowrate variation with each propellant injection pressure drop were studied;the effects of the injectors' configuration on the flowrate coefficient were analyzed,the injectors' flowrate characteristics in tripropellant operating condition were compared with those in bipropellant operating condition;the pressure of the dual-fuel premixed cavity of the swirl injector with premixed fuel injection was measured and the flowrate characteristics of the injector were analyzed.The conclusions obtained in this paper provide an important reference for the optimization design of the tripropellant injectors and the gas/liquid coaxial injectors.

关 键 词：液体推进剂火箭发动机 喷嘴 流量测量 冷流试验 研究 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]