摘要
对 8种进口M数为 2 .5的超燃冲压发动机模型燃烧室在各种驻点条件和燃料总体当量比下进行了实验 ,燃烧室构型、燃料壁面注射、支板注射、凹腔火焰稳定结构对发动机的性能影响进行了研究。一维简化模型进一步提出用于数据处理与分析 ,计算与实验结果基本上一致 ,对影响燃烧效率与总压损失的各因素进行了讨论。
Supersonic combustion experiments of a fixed entry Mach number 2.5 were conducted using eight model combustors, at various stagnation conditions and global equivalence ratio. Effects of wall injection, strut injection, and cavity flameholder were systematically investigated. A one-dimensional model was further proposed for data reduction and analysis. The calculated results are fairly consistent with the experimental measurements. Performance of various model combustor as well as the factors affecting combustion efficiency and total pressure recovery were discussed.
出处
《流体力学实验与测量》
CSCD
2000年第1期72-80,共9页
Experiments and Measurements in Fluid Mechanics
基金
国家自然科学基金重点资助项目! ( 1 97892 0 2 )
