为了研究空燃比对固体火箭超燃冲压发动机补燃室性能的影响,文中对不同空燃比下补燃室掺混燃烧流场进行了模拟。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,化学反应速率随着空燃比的增加而增大;燃烧效率与总压恢复系数随着空燃比的增大而增大;补燃室推力与比冲也随着空燃比的增大而增大。空燃比的选择原则是保证导弹武器的推阻比最佳。
In this work, we simulated the mixing combustion flow field of second combustor under different air-fuel ratio to study the influence of air-fuel ratio on the second combustor performance of solid-rocket scramjet. The mixing combustion of the second combustor was simulated by using the two order upwind scheme based on the density, and the turbulence model and combustion model adopted SST k-ω model and eddy dissipation model, respectively. The result indicated that the chemical reaction rate, combustion efficiency, and total pressure recovery coefficient increased with the increase of air-fuel ratio. In a word, the selection principle of air-fuel ratio is to ensure the thrust-drag ratio is the best
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[1] 解发瑜, 李刚, 徐忠昌. 高超声速飞行器概念及发展动态[J].飞航导弹, 2004(5): 27-31.
[2] 赵庆华, 刘建全, 王莉莉, 等. 固体燃料的超声速燃烧研究进展[J].飞航导弹, 2009(10): 59-63.
[3] 吕仲, 夏智勋, 刘冰, 等. 采用固体燃料的超燃冲压发动机研究进展[J].航空动力学报, 2016, 31(8): 1973-1984.
[4] LYU Zhong, XIA Zhixun, LIU Bing, et al. Experimental and numerical investigation of a solid-fuel rocket scramjet combustor[J].Journal of Propulsion and Power, 2015, 32(2): 1-6.
[5] 吕仲. 固体火箭超燃冲压发动机工作特性研究[D].长沙: 国防科学技术大学, 2012.
[6] 李轩, 马利锋, 赵永涛, 等. 固体火箭超燃冲压发动机性能数值模拟研究[J].弹箭与制导学报, 2014, 34(1): 104-108.
[7] 刘仔, 陈林泉, 吴秋. 来流参数对固体火箭超燃冲压发动机补燃室性能的影响[C]//中国宇航学会火箭发动机专业委员会. 第33届固体火箭推进专业学术年会论文集,[出版社地不详]:[出版者不详].2016: 58-65.
[8] 陶欢. 固体燃料超燃冲压发动机燃烧室工作特性研究[D].北京: 北京理工大学, 2015.
[9] EVANS J S, SCHEXNAYER J C, BEACH H L. Applicaton of a two-dimensional parabolic computer program to prediction of turbulent reacting flows:NASA 1169[R].[S.l.:s.n.],1978.
[10] 王新月. 气体动力学基础[M].西安: 西北工业大学出版社, 2006: 210-214.