Scramjet整机流场的非结构网格并行数值模拟

Numerical parallel simulations of whole scramjet flowfields on unstructured grids

关键词:  超燃发动机  非结构网格  支板  湍流反应流  并行计算  旋涡

Key words:  Scramjet  Unstructured grid  Strut  Turbulent reacting flow  Parallel simulations  Vortex

摘要:

为了得到某支板喷氢超燃冲压发动机内流场的细节,采用非结构网格CFD隐式解算器,耦合求解Na-vire-Stokes方程、组分连续方程和M enter的k-ω应力剪切传输(SST)湍流模型,对整机模型的冷流和三个当量油气比的湍流反应流进行了三维并行模拟。给出了流线和水的分布云图,分析了支板附近旋涡和推进流道一维质量加权平均的马赫数、静温、组分质量分数及燃烧效率等参数随当量油气比的变化,并将壁面压力和实验值进行了比较,吻合较好。除=0.8在支板附近出现了小范围亚声速外,其余状态整个内流道超声速占主流。

Abstract:

An unstructured CFD solver which employs an implicit finite volume method to solve the complete Navire-Stokes,species and Menter’s k-ω Shear Stress Transport(SST) equations in a fully coupled manner was applied to the 3-D parallel simulations of the cold and turbulent reacting flows of three fuel/air equivalence ratios  of a whole hydrogen fueled scramjet engine to get the flow information.Streamlines and H2O contours distributions were gained.Variations of vortexes near the strut and 1-D mass-weighted parameters in the flow path of the scramjet such as Mach number,static temperature,mass fraction of species and combustion efficiencies with the equivalence ratio were analyzed.Wall pressures were compared with the experimental data and they agree well.All flows are supersonic dominated except small subsonic region near the strut for =0.8.