超燃冲压发动机等截面隔离段流动特性的LBM模拟  

Lattice-Boltzmann method for simulation of flow characteristic in constant area isolator of scramjet

作　　者：冯永昌[1] 李会雄[1] 贺宏[2] 

机构地区：[1]西安交通大学能源与动力工程学院动力工程多相流国家重点实验室,西安710049 [2]中国航天科技集团公司第六研究院第165所,西安710100

出　　处：《航空动力学报》2013年第3期681-687,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(51111120092)

摘　　要：为了探寻研究超燃冲压发动机隔离段内复杂流动的新方法,采用耦合的双分布函数格子-Boltz-mann方法(LBM)对不同条件下隔离段内的流动进行了研究,分析了出口反压、进口马赫数、进口附面层厚度对隔离段流动特性的影响.结果表明:随着出口反压、进口附面层厚度的增加,以及进口马赫数的减小,可使激波串起始位置前移.结果说明耦合的双分布函数LBM有望成为研究超燃冲压发动机内复杂流场的一种有效的数值模拟手段.In order to seek a new method to study the complex flow field of isolator,the influence of flow parameters upon the internal flow field of isolator under different conditions was studied by numerical simulation with coupled double distribution function lattice-Boltzmann method（LBM）,and the parameters included the back pressure,entrance Mach number,and boundary layer thickness.The results show that with the increase of the back pressure and boundary layer thickness or with the decrease of entrance Mach number,shock train would move upwards along the isolator.From this study,it can be concluded that the coupled double distribution function LBM is an efficient approach for simulating the complex flow field of scramjet.

关 键 词：LBM(lattice-Boltzmann method) 双分布函数 超燃冲压发动机 隔离段 数值模拟 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]