Abstract: 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

Key words: Liquid propellant rocket engine;Combustion chamber;Parallel computing;Flow field simulation

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。

关键词: 液体推进剂火箭发动机;燃烧室;并行计算;流场仿真