Viscous Drag Reduction in a Scramjet Combustor with Film Cooling
Viscous Drag Reduction in a Scramjet Combustor with Film Cooling
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DOI：
10.2514/6.2001-1818
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发表时间：
2001-04
期刊：
影响因子：
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通讯作者：
S. Rowan;A. Paull
中科院分区：
文献类型：
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作者：
S. Rowan;A. Paull
在超燃冲压发动机圆柱燃烧室上进行了实验研究，研究了孔缝喷射和氢气燃烧对粘性阻力的影响。在昆士兰州大学的T4自由活塞激波风洞中，在名义自由飞行马赫数为4.4、滞止焓为5.9 MJ/kg的条件下，对设计成提供不同缝当量比的喷油器进行了试验。每个燃料喷射器在总当量比的范围内进行测试，并且使用单分量应力波力天平测量积分阻力。对长度为220、420和520毫米的燃烧室进行了试验。此外，通过改变流动的滞止压力和滞止焓，分别研究了飞行高度和速度变化对流动的影响。对于每种喷射器，在总当量比的低值处观察到粘性阻力的最大减小。增加槽当量比导致阻力减少水平略有增加。燃烧室长度变化的结果与预期趋势一致。然而，阻力测量的不确定性使得很难解释滞止压力和焓的变化结果。
Experiments have been performed on a cylindrical scramjet combustor to investigate the effect of porthole and slot injection and combustion of hydrogen on viscous drag. Fuel injectors designed to provide different slot equivalence ratios were tested at a nominal freestream Mach number of 4.4 and stagnation enthalpy of 5.9 MJ/kg in the T4 free piston shock tunnel at The University of Queensland. Each fuel injector was tested over a range of total equivalence ratios and the integrated drag force was measured using a single component stress wave force balance. Experiments were performed for combustor lengths of 220, 420 and 520 millimetres. In addition, the stagnation pressure and enthalpy of the flow were varied to investigate the effect of changes in flight altitude and velocity respectively. For each injector, the greatest reduction in viscous drag was observed at low values of the total equivalence ratio. Increasing the slot equivalence ratio resulted in slightly increased levels of drag reduction. Results for variation in combustor length agreed with expected trends. However, the uncertainty in the drag measurements made it difficult to interpret the results for variation in stagnation pressure and enthalpy.