Large Eddy Simulation of Supercritical Mixing and Combustion for Rocket Applications
Large Eddy Simulation of Supercritical Mixing and Combustion for Rocket Applications
复制标题
火箭应用超临界混合和燃烧的大涡模拟
DOI：
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发表时间：
2014
期刊：
影响因子：
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通讯作者：
M. Ihme
中科院分区：
文献类型：
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作者：
Jean;M. Ihme
我们向CharlesX报告了真实流体能力的实施情况，CharlesX是斯坦福大学湍流研究中心使用的内部非结构化大涡模拟代码。对于纯混合和小火焰/进度变量(FPV)模型燃烧情况，需要一个概念上不同的实施方案。对于非反应模拟，采用基于牛顿-拉夫森的迭代算法，根据输运密度和能量确定温度。对于反应模拟，使用了扩展的火焰面表格，该表格列出了偏离函数以及压缩系数。这些列表参数被用来修正输送的热力学性质。使用CharlesX的实际流体延伸来调查一个无反应和一个反应的病例。在这两种情况下，二阶基本无振荡(ENO)格式被局部应用于用双阈值相对密度传感器识别的面上的通量计算。这避免了数值解在有限的数值耗散下的虚假振荡。这项初步工作说明了CharlesX在典型火箭发动机配置中捕获重要物理信息的能力。
We report on the implementation of the real fluid capabilities to CharlesX, the in-house, unstructured, large eddy simulation code used at the Center for Turbulence Research at Stanford University. A conceptually distinct implementation was needed for the puremixing and the flamelet/progress-variable (FPV) model combustion case. For the nonreacting simulations, a Newton-Raphson based iterative algorithm is used to determine the temperature from the transported density and energy. For the reacting simulations, an extended flamelet table is used that tabulates the departure functions as well as the compressibility factor. These tabulated parameters are used to correct the transported thermodynamic properties. The real fluid extension to CharlesX was used to investigate a non-reacting and a reacting case. In both of these cases, a second-order essentially nonoscillatory (ENO) schemes is locally applied to the flux computation on the faces identified with a dual-threshold relative density sensor. This avoids spurious oscillations of the numerical solution with limited numerical dissipation. This preliminary work illustrates the capability CharlesX to capture the important physics in a typical rocket engine configuration.