非壅塞固体火箭冲压发动机二次燃烧室进气方案研究

Study on secondary combustion chamber air-inlet scheme of unchoked solid rocket ramjet

用k ε湍流模型以及EBU燃烧模型,对固体火箭冲压发动机二次燃烧三维反应流场进行了数值计算,研究了空气射流与富燃燃气射流动量之比、射流速度和燃气发生器喷管数量对二次燃烧的影响。研究结果表明,当空燃动量比在一定范围内时,若空燃动量比变大,则二次燃烧效率升高;降低空气和燃气射流的速度有利于二次燃烧效率的提高;并且增加燃气发生器喷管数量能增强燃气与空气在头部的掺混效果,为燃烧创造良好的条件。

Three-dimension reaction flow-field of secondary combustion for solid rocket ramjet is numerically calculated by using k-ε two-equation model and EBU combustion model. The effects of air-fuel momentum ratio, fluidic velocity and gas generator nozzle numbers on secondary combustion is investigated. The results show that increase of air-fuel momentum ratio within proper range and decrease of air-fuel fluidic velocity can improve combustion efficiency, increase of nozzle numbers of gas generator is beneficial to enhance the air-fuel mixing effect in forward region and produce good combustion condition.