液体煤油超声速燃烧的三维数值分析  

Three-Dimensional Numerical Analysis of Liquid Kerosene Supersonic Combustion

作　　者：胡欲立[1] 刘欧子[2] 蔡元虎[2] 

机构地区：[1]西北工业大学航海学院,西安710072 [2]西北工业大学动力与能源学院,西安710072

出　　处：《燃烧科学与技术》2007年第3期214-219,共6页Journal of Combustion Science and Technology

基　　金：国家自然科学基金资助项目(50086002);西北工业大学博士论文创新基金资助项目(200219)

摘　　要：利用计算流体力学软件对煤油在双模态超声速燃烧室内的超声速喷雾燃烧进行数值模拟.采用离散液滴模型、概率密度函数紊流扩散燃烧模型和紊流k-ω模型,在飞行马赫数为5、煤油与空气的当量比为0.551时的超声速燃烧进行了计算.计算得到的壁面静压分布与实验数据十分接近;总压力损失系数是0.70,小于实验测量值0.707;分析数值结果可知,支板喷油和凹槽火焰稳定器提高了混合和燃烧效率,燃烧室出口燃烧效率达0.62,接近实验得到的燃烧效率0.696.With the Fluent software,numerical analysis of the kerosene spray supersonic combustion was carried out in the dualmode supersonic combustor. At the condition, that is, the flight Mach number of 5 and the fuel-air equivalence ratio of 0.551, the numerical results were gotten with the probability density function（PDF） turbulence and chemistry interaction model, k-ω turbu- lence model and the discrete droplet model. The wall static pressure of the experiment is of agreement with that of the numerical results, and the numerical total pressure loss coefficient of 0.70 is lower than the experimental value of 0.707. Be numerical resuits show the strut and cavities can improve the mixture and combustion, and the combustion efficiency of the combustor exit is 0.62, which is close to the experimental value of 0.696.

关 键 词：超声速燃烧冲压发动机 双模态 超声速燃烧 亚声速燃烧 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]