燃气喷射方式对固体火箭超燃冲压发动机性能的影响  

Effect of gas injection way on the solid-rocket scramjet performance

作　　者：刘仔[1] 陈林泉[1] 褚佑彪[1] 李伟 LIU Zai;CHEN Linquan;CHU Youbiao;LI Wei(The 4IS'Institute of the Fourth Academy of the CASC,Xi'an 710025,China)

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2018年第6期710-714,共5页Journal of Solid Rocket Technology

摘　　要：利用数值模拟方法研究了不同喷孔参数对固体火箭超燃冲压发动机补燃室性能的影响。采用基于密度的二阶迎风格式对补燃室掺混燃烧过程进行模拟,湍流模型和燃烧模型分别采用SST k-ω模型和涡团耗散模型。计算结果表明,喷孔数量、喷射角度θ以及喷孔分布半径r对补燃室的掺混燃烧性能均存在明显影响;其中,喷射角度θ对补燃室掺混燃烧性能的影响最大;存在最佳的喷孔数量使得燃烧效率最大;随着喷射角度θ与喷孔的分布半径r的增加,燃烧效率逐渐增加,但总压恢复系数逐渐减小。The effect of different nozzle parameters on the performances of solid-rocket scramjet second combustor has been studied through numerical simulation method.Density-based second order upwind was applied to simulate the mixing combustion process in the secondary combustor.The turbulence and combustion models adopted SST κ-ω model and vortex dissipation model,respectively.The calculation results show that there is significant effect of the nozzle number,injection angle (θ),and distribution radius (r)of nozzle on the mixing combustion performances in secondary combustor.The injection angle has the greatest impact on the mixing combustion performance in second combustor.There is an optimal nozzle number to make combustion efficiency maximum.As the increase of injection angle (θ)and distribution radius (r)of nozzle,the combustion efficiency gradually increases,while the to- tal pressure recovery coefficient gradually decreases.

关 键 词：固体火箭超燃冲压发动机 喷孔数量 喷射角度 喷孔分布半径 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]