超燃冲压发动机燃烧模态转换试验研究

Combustion mode transition in a scramjet engine

在模拟飞行高度为25 km、来流马赫数为6的情况下,采用试验研究的方法对超燃冲压发动机燃烧模态转换进行了直连式试验。根据燃烧室壁面压力分布和一维模型分析表明。燃料喷射位置和当量比的动态改变.实现了燃烧室内燃烧模态的动态转换。不同燃料喷射位置切换顺序比较表明,燃烧室内燃烧状态的改变受燃料分布所决定,但是燃烧室自身具有一定的抗波动能力。

The transition processes of supersonic combustion in a dual-mode scramjet were investigated by means of directly-connected tests under the simulated conditions corresponding to the flying altitude of 25 km and the Mach number of 6. Pressure distribution on the wall of the combustor and one- dimensional simulation indicate that the combustion mode transition can be carried out by altering fuel injection position and equivalence ratio. Comparison of switch sequences of different fuel-injection position shows that the combustion mode changes are determined by the fuel distribution in a combustor, but the combustor has a certain ability to resist fuel disturbance.