模型加力室大涡模拟的并行计算  

Parallel Computation for Large-Eddy Simulation of a Model Afterburner

作　　者：邵茂敏[1] 颜应文[1] 刘勇[1] 赵坚行[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空动力学报》2006年第3期497-501,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助(5176017)

摘　　要：采用基于M P I(消息传递库)的并行算法,在贴体网格下对带V形槽稳定器模型加力燃烧室紊流化学反应流场进行数值模拟,湍流模型采用k方程亚网格尺度模型,燃烧模型采用亚网格EBU模型,采用热通量辐射模型估算辐射通量。在程序设计中,采用动态内存分配、分区算法和多点重合交错网格系统,并行计算的结果与单机运行结果的对比表明计算结果是正确的,可以明显的提高运算效率,是解决复杂燃烧流动大规模数值模拟的有效手段。Large-Eddy Simulation （LES） of turbulent chemically reacting flows in the model afterburner with V-gutter flame holder was carried out using parallel algorithm based on the MPI （Message Passing Interface） library. The k-equation subscale grid model was used to simulate the turbulent viscosity. The chemical reaction rate was determined by the subgrid EBU combustion model and the heat flux model was employed for the heat flux. In the computer cluster, overlapping grid method was applied to treat the staggered grid in the common boundary. The dynamic memory allocation was used to reduce memory usage. The parallel computing and sole computing results were compared. It shows that parallel computation procedure can correctly simulate the chemically reacting process in the model afterburner. Also, the computation time con- sumed is dramatically reduced. Parallel computation is proved to be an effective way to simulate the turbulent flows and combustion process in the complex geometry combustor.

关 键 词：航空 航天推进系统 MPI(Message PASSING Interface) 大涡模拟 并行计算 加力燃烧室 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]