同轴双剪切气-气喷嘴试验研究  

Experimental investigation on dual shear coaxial gas-gas injector

作　　者：杜正刚[1] 高玉闪[1] 李茂[1] 汪小卫[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2010年第2期170-173,共4页Journal of Propulsion Technology

摘　　要：为研究应用于全流量补燃循环发动机的新型结构气-气喷注器,对以气氢和气氧为推进剂的同轴双剪切喷嘴进行试验研究,分析喷嘴不同中心氢流量比例和流量变化对推进剂燃烧效率的影响。结果表明:中心氢流量与外圈氢流量的比例是同轴双剪切喷嘴重要的设计参数。当中心氢流量比例为0.3至0.4之间时,同轴双剪切喷嘴使推进剂高效燃烧;在喷嘴流量相当于航天飞机主发动机单喷嘴8倍的工况下,同轴双剪切喷嘴能使推进剂达到高的燃烧效率。In order to develop the new pattern gas-gas injector for full flow staged combustion cycle engine,experimental investigation was conducted on the dual shear coaxial injector in which the gaseous oxygen and hydrogen were used as propellants. The effects of the center hydrogen ratio as well as total mass flowrate of injector on combustion efficiency were analyzed. The results showed that the ratio of center hydrogen mass flowrate to the total hydrogen mass flowrate was a key parameter for dual shear coaxial injector. At the fraction between 0.3 and 0.4,the propellants combusted efficiently. High combustion efficiency can be obtained with this type of injector at the condition of large mass flowrate close to eight times as that of space shuttle main engine with single element injector.

关 键 词：流量 喷嘴 效率 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]