Massively Parallel Simulations of Kerosene-Fueled Model Scramjet
Massively Parallel Simulations of Kerosene-Fueled Model Scramjet
复制标题
DOI：
10.2514/6.2005-3318
复制
发表时间：
2005-05
影响因子：
3.3
通讯作者：
L. Jialing;Yang Shun-hua;Li Weixiong;Xing Jianwen;China Aerodynamics
中科院分区：
文献类型：
--
作者：
L. Jialing;Yang Shun-hua;Li Weixiong;Xing Jianwen;China Aerodynamics
对三维模型超燃冲压发动机进行了大规模并行数值模拟。本研究的目的是验证CARDC的CFD程序及其物理和化学模型。对所研究的三种情况进行了计算，使用了两种碳氢燃料乙烯和煤油的三种结构。第一种构型与A.A.Taha相同，第二种构型仅用于湍流模型比较，而第三种煤油模型超燃冲压发动机与本实验所用构型相同。本文采用并行三维CFD程序，采用格心有限体积法求解雷诺平均守恒方程。无粘通量计算采用三阶MUSCL格式，采用Steger-Warming通量分裂格式；粘性通量计算采用中心差分方法。采用修正的Wilcox的ω−-k两方程湍流模型模拟湍流效应。第一次和第二次计算是在128个CPU的COW上进行的，第三次计算是在SZ MPP机器上进行的，使用了512个CPU。计算结果表明，现有的CFD程序及其合理的物理和动力学模型能够预测超燃冲压发动机模型的复杂燃烧流型和潜在性能。
Massively parallel numerical simulations of three-dimensional model scramjets are presented. The objective of this study is to validate CARDC’s CFD code and its physical and chemical models. The computation of three cases under investigation was performed, which used three configurations with two types of hydrocarbon fuel, ethylene and kerosene. The first configuration with gaseous ethylene injection was the same as that of A. A. Taha, the second configuration with kerosene was computed only for comparison of turbulent models, while the third one of kerosene fueled model scramjet was the same as that used in our experiment. The parallel 3-D CFD code, which solves the Reynolds-averaged conservation equations with a cell-center finite volume method, is used in this research. The inviscid fluxes are computed using a 3rd-order MUSCL with Steger-Warming flux-splitting scheme; the viscous fluxes are evaluated using central differences. The modified Wilcox’s ω − k two-equation turbulence model is used to simulate the effect of turbulence. The first and second computation was performed on a COW with 128 CPUs and the third computation was performed on SZ MPP machine using 512 CPUs. All the computed results show that the current CFD code with its reasonable physical and kinetic models is able to predict the complex combustion flow patterns and potential performance of the scramjet model.