论文部分内容阅读
为了清晰地描述超声速条件下的复杂流动与燃烧过程,建立了基于IDDES模型和火焰面/进度变量模型的湍流燃烧数值模拟方法,并应用于德国宇航中心(DLR)超燃冲压发动机的数值模拟。计算结果与实验数据符合良好,表明该方法可以较为准确地描述超声速湍流燃烧过程,也验证了经过可压缩性修正的火焰面/进度变量模型适用于超声速燃烧问题的求解。同时,利用k-ωSST模型对同一算例进行了计算,发现其对物理量分布的计算精度要低于IDDES模型,说明湍流输运过程的描述对火焰面/进度变量模型的计算精度有重要影响。
In order to clearly describe the complicated flow and combustion process under supersonic velocity, a numerical simulation method of turbulent combustion based on IDDES model and flame surface / progress variable model was established and applied to the numerical simulation of DLR scramjet. The calculated results are in good agreement with the experimental data. It shows that this method can describe the supersonic turbulent combustion process more accurately, and also verifies that the compressibility-modified flame plane / process model is suitable for solving the supersonic combustion problem. Meanwhile, using the k-ωSST model to calculate the same example, it is found that the calculation accuracy of the physical quantity distribution is lower than that of the IDDES model, which shows that the description of the turbulent transport process has an important influence on the calculation accuracy of the flame plane / progress variable model.