Scramjet free-jet test process at Ma10 conditions
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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。
Abstract: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.
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Key words:
- scramjet /
- high Mach number /
- ignition /
- combustion /
- test process
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图 6 唇口前壁面压力p31和壁面热流密度φ18的时间历程
Figure 6. Time histories of wall pressure p31 and wall heat flux φ18 upstream of the inlet lip
图 9 非设计来流条件下的流场纹影图像
Figure 9. Schlieren images of flow fields under off-design condition
图 10 燃烧室出口压力p46和壁面热流密度φ39的时间历程
Figure 10. Time histories of wall pressure p46 and wall heat flux φ39 at combustor outlet
图 12 不同当量比下的发动机壁面压力分布
Figure 12. Pressures distributions of engine wall with different equivalent ratios
图 13 不同当量比的发动机壁面热流密度分布
Figure 13. Heat flux distributions of engine wall with different different equivalent ratios
表 1 FD-14A高焓激波风洞喷管出口气流条件
Table 1. Parameters of FD-14A high-enthalpy shock wave wind tunnel
Ma q/kPa T0/K p0/MPa 10 30 3580 30 
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