固体火箭超燃冲压发动机补燃室构型的影响分析  

Configuration effects analysis of the second combustor of the solid rocket scramjet

作　　者：刘仔[1] 陈林泉[1] 吴秋[1] 王立武[1] 

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》2017年第4期432-436,共5页Journal of Solid Rocket Technology

摘　　要：针对不同补燃室结构参数对固体火箭超燃冲压发动机补燃室掺混燃烧性能的影响进行研究,分析各级燃烧室的长度与扩张角度对补燃室性能的影响。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。结果表明,提高燃烧效率与降低总压损失是相互矛盾的;燃烧效率随燃烧室长度的增加而增大,随燃烧室扩张角度的增加而减小;总压恢复系数随燃烧室长度的增加而减小,随燃烧室扩张角度的增加而增大;一级燃烧室的结构参数对燃烧效率与总压恢复系数的影响最大。当补燃室的总长与出口面积一定时,以发动机的总体性能参数作为补燃室构型的优化目标,对一、二级燃烧室长度与一、三级燃烧室扩张角度进行优化。In this work,we studied the influence of different combustor configuration parameters on the mixed combustion performance of the second combustor of the solid-rocket scramjet engine.We further analyzed the influence of the length and expansion angle of the combustor at all levels on the combustion performances of the combustor.The mixed combustion of the combnstor was simulated by using a two-order upwind scheme based on the density.The turbulence model and combustion model were introduced to SST k-ω model and eddy dissipation model, respectively.The result suggested that improving combustion efficiency and reducing total pressure loss were contradictory.The combustion efficiency increased with the increase of combustor length, while decreased with the increase of combustor expansion angle.The total pressure recovery coefficient decreased with the increase of combustor length, while increased with the increase of combustor expansion angle.The structure parameters of the first stage combustor had the largest influ- ence on the combustion efficiency and total pressure recovery coefficient. When the total length and the outlet area of the second combustor were at a certain value, the length of the first and second combustor and the angle of the first and third combustor were optimized by using the overall performance parameters of the engine as the optimization goal of the second combustor.

关 键 词：补燃室 固体火箭超燃冲压发动机 燃烧效率 总压恢复系数 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]