超声速气流中煤油燃烧的实验研究

为了得到双模态超燃冲压燃烧室模型在不同飞行马赫数时的性能参数，在直连式风洞中，飞行马赫数为4，5，6的来流条件下，对液体煤油的超声速燃烧进行研究。对于试验的三种热态工况，液体煤油实现了点火，并稳定燃烧；并且其工作状态都是典型的亚燃冲压模态。通过一维模型对壁面静压进行分析，得到了燃烧室流场参数和性能参数。在各个飞行马赫数和当量比条件下，燃烧室出口总压损失分别是0．565，0．696和0．725，都接近试验测量值；燃烧室出口的燃烧效率分别为0．82，0．67和0．60。不同飞行马赫数下双模态燃烧室试验数据和参数，为其性能的进一步改进提供了实验依据。

Experimental investigation of kerosene fuel combustion in the supersonic flow

For the dual-mode scramjet it is important to conduct experimental research for its combustor. In order to get the performance parameters of the dual-mode combustor model at the different flight Mach, the investigation of liquid fuel kerosene was carried out in the combustor direct-connect wind tunnel. In the non-cold state cases, fuel kerosene realized ignition and stable combustion, the normal shock wave series appeared in the isolator and these operating processes were the typical ramjet modes. With one-dimensional analysis method, the flow field parameters, the total pressure loss coefficient and combustion efficiency were estimated in terms of the measured wall static pressure data. At the combustor outlet, the total pressure loss coefficients of the non-cold state cases were 0.565, 0.696 and 0.725, respectively and consistent with the experimental measurement values. The combustion efficiencies were 0.82, 0.67 and 0.60, respectively. With the data and parameters of the dual-mode combustor, its performance could be improved.