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为了研究修正的火焰面反应进度变量燃烧模型在超声速湍流扩散燃烧问题中的适用性,对德国宇航中心(DLR)超声速燃烧室开展RANS数值模拟。基于Open Foam软件平台中密度求解器分别对三维冷态场和燃烧场进行模拟分析。将网格自适应加密技术用于流场的计算;燃烧场计算中,通过分析不同压力下层流火焰面数据库,引入了反应进度变量源项的压力修正系数,压力修正系数α等于2.2。计算结果表明,冷态场中压力分布、波系分布、速度分布以及燃烧场中波系分布、速度分布、温度分布结果均与实验值符合较好。压力修正方法能够较好地解决超声速湍流扩散燃烧问题。湍流Schmidt数敏感性分析表明,湍流Schmidt数Sct对湍流火焰结构有较大影响,文中Sct等于0.7时能得到与实验值较为一致的分布。
In order to investigate the applicability of the modified flame surface reaction progress variable combustion model to the supersonic turbulent diffusion combustion problem, a numerical simulation of RANS was performed on a DLR supersonic combustion chamber. Based on Open Foam software platform density solver, the 3D cold field and combustion field are simulated respectively. In the calculation of combustion field, the pressure correction coefficient of the source term of reaction progress variable was introduced by analyzing the laminar flame surface database under different pressures. The pressure correction coefficient α is equal to 2.2. The calculation results show that the pressure distribution, wave distribution, velocity distribution and the distribution of wave system in the cold field, the velocity distribution and the temperature distribution are in good agreement with the experimental data. Pressure correction method can better solve the problem of supersonic turbulent diffusion combustion. The results of turbulent Schmidt number sensitivity show that the turbulent Schmidt number Sct has a great influence on the turbulent flame structure. When Sct is equal to 0.7, the consistent distribution with the experimental value is obtained.