液体发动机燃烧室流场模拟的并行SIMPLE算法  

PARALLEL SIMPLE ALGORITHM FOR COMPLEX FLOW SIMULATION IN LIQUID ROCKET ENGINE CHAMBER

作　　者：赵文涛[1] 王正华[1] 杨晓东 

机构地区：[1]国防科技大学并行与分布处理国家重点实验室,长沙410073

出　　处：《推进技术》1999年第6期16-18,共3页Journal of Propulsion Technology

摘　　要：用串行和并行ＳＩＭＰＬＥ算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。控制方程组用欧拉坐标系下的Ｎ－Ｓ方程组描述。在并行虚拟机环境下研究了交错网格系统中参数的传输和接受模式， 从计算结果可以看出并行计算的效率较高， 是解决此类复杂流动大规模数值模拟问题的有效手段之一。The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine.The controlling equations were described under the Euler coordinate.The sending and receiving mode of flow fields parameters in the staggered grid were studied.The results show that parallel computation efficiency is reasonably high and parallel computing is a useful method to such large scale numerical simulation problem of complex flow

关 键 词：液体发动机 燃烧室 流场模拟 并行SIMPLE算法 

分 类 号：V434.22[航空宇航科学与技术—航空宇航推进理论与工程]