摘要
基于中国空气动力研究与发展中心的高焓激波风洞(FD-14A)在毫秒量级试验时间内,开展了模拟飞行马赫数为10,动压为30 kPa条件下的超燃冲压发动机自由射流试验研究。采用高速纹影和高速摄影捕捉了进气道唇口波系和燃烧室火焰的时间发展历程,结合发动机壁面压力和热流密度数据,分析了该工况下发动机的工作过程。测量了多种燃料当量比下的发动机壁面压力和热流密度,试验结果表明:在当量比0.50~1.37的宽范围下均实现了可靠点火和稳定燃烧。
Scramjet free-jet tests were conducted in milliseconds in the high-enthalpy shock wave wind tunnel(FD-14A)of China Aerodynamics Research and Development Center at the conditions of replicating flight Mach number 10 and dynamic pressure of 30 kPa.High-speed schlieren and high-speed photography were employed to record the shock waves at the inlet lip and flame spreading process in the combustor,respectively.The free jet test process was analyzed by the optical measurement,scramjet wall pressures and heat fluxes.The ignition and combustion tests were conducted with different equivalent ratios of hydrogen.Distributions of pressures and heat fluxes along the engine wall indicated that ignition and stable combustion were achieved within a wide range of fuel equivalent ratios from 0.50 to 1.37.
作者
张冬青
邓维鑫
邢建文
何粲
ZHANG Dongqing;DENG Weixin;XING Jianwen;HE Can(Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2023年第3期735-742,共8页
Journal of Aerospace Power
基金
智强基金。
