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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 study a new type of structure gas-air injector applied to a fully-fledged burn-in engine, a coaxial double-shear nozzle with gas-hydrogen and oxygen-oxygen propellants was used to study the effects of hydrogen flow rate and flow rate Effect on Propellant Combustion Efficiency. The results show that the ratio of the central hydrogen flow to the outer hydrogen flow is an important design parameter of the coaxial double-shear nozzle. When the ratio of hydrogen flow in the center is between 0.3 and 0.4, the coaxial double-shear nozzle burns the propellant efficiently. Under the condition that the nozzle flow rate is equivalent to 8 times of the space shuttle main engine single nozzle, the coaxial double-shear nozzle can Enable propellant to achieve high combustion efficiency.