亚燃冲压模型燃烧室高空负压试验

Experiment of Ramjet Model Combustor Under High Altitude and Low Pressure Condition

为了验证亚燃冲压燃烧室在高空负压条件下稳定工作的能力,设计了带蒸发式值班火焰稳定器与直射式喷油装置的亚燃冲压模型燃烧室,对该模型燃烧室进行了冷态流阻试验、贫油熄火边界试验以及不同截面燃烧效率试验研究。研究结果表明,试验件的冷态流阻系数略大于1,冷态总压恢复系数0.98以上;蒸发式火焰稳定器贫油熄火边界较宽;两截面燃烧效率最低相差6%,最高相差19%,在高空负压条件下,增加燃烧段长度能显著提高燃烧效率。

Cold flow resistance experiment,lean blowout experiment and combustion efficiency experiment were conducted on ramjet model combustor with evaporative flame holder and direct fuel injection.Through these experiments,the ability of ramjet combustor stabilization under high altitude and low pressure condition was validated.The investigation results show that the coefficient of cold flow resistance is slightly more than 1 and the coefficient of cold total pressure recovery is more than 0.98.The lean blowout of the evaporative flame holder is wide.The least difference of combustion efficiency of two sections is 6% and the most difference is 19%.Combustion efficiency is evidently enhanced by increasing combustion length under high altitude and low pressure condition.