超声速燃烧室燃烧压力影响因素试验研究

采用试验研究的方法．在模拟飞行高度25km、来流马赫数6的情况下．在直连式试验台上对超燃冲压发动机燃烧室压力影响因素进行了初步研究。结果表明．燃料喷射位置的变化，改变了燃烧室内的放热区域，从而影响了燃烧室内的压力分布；在一定燃料当量比范围内．当量比越大燃烧室压力越高，但是当量比与燃料喷注压降耦合影响压力分布；在燃烧室后段设置深凹腔有利于提高燃烧室压力。

Experimental Investigation on the Wall Pressure Influential Factors of Supersonic Combustion

The preliminary study on the influential factors of scramjet combustor wall pressure was carried out on the direct-connected test facilities under the simulated condition of 25km, 6Ma. The study shows that exothermic region is changed by positional change of fuel injection so as to affect pressure distribution in the combustor. In a desired range, the bigger equivalence ratio, the higher wall pressure, but coupled with fuel injection pressure. The investigation also reveals that deep reentrant installation at the tail of combustor is good for higher wall pressure.