超音速燃烧室燃烧效率数学模型及气流状态参数的计算  

THE MODEL OF COMBUSTION EFFICIENCY AND CALCULATION OF FLOW PROPERTIES FOR SCRAMJET COMBUSTOR

作　　者：刘陵[1] 张榛[1] 牛海发[1] 刘敬华[1] 

机构地区：[1]西北工业大学

出　　处：《推进技术》1989年第2期1-7,共7页Journal of Propulsion Technology

摘　　要：本文分析及提出了超音速燃烧冲压发动机燃烧室燃烧效率的数学模型.该模型综合了氢气喷射方式、燃烧室进口气流参数以及燃烧室结构的影响因素.用这一数学模型求解一组一元流方程.计算出通过燃烧室的气流状态参数,计算结果与试验数据对比,证明这个模型是适用的.The model of combustion efficiency for scramjet combustor is analyzed and presented in this paper.The model involves effect factors of fuel injection, entrance conditions and combustor configuration.Using the model of combustion efficiency the resulting (one-dimensional) flow properties is computed step by step through the combustor.The comparisor of the experimental results and theoretical predictions indicates that the theory is adequate.

关 键 词：超音速燃烧 冲压喷气发动机 燃烧室 数学模型 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]