The algebraic multigrid method was used to solve the pressure correction equation of the compressible form SIMPLE algorithm. The Navier-Stokes equations were dispersed on the basis of collocated grid finite volume method.The 3D flow field of com-bustion chamber and nozzle in a dual burning rate star grain solid rocket motor was numerically simulated. Through the comparison with the direct method and Incomplete LU ( ILU) factorization preconditioning BiConjugate Gradient Stabilized ( BiCGStab) algo-rithm in different grid size,the computational efficiency of solving such problems by algebraic multigrid method was demonstrated. The results of comparison with other methods show that algebraic multigrid method increases the efficiency of solving the three-di-mensional flow field in solid rocket motor.Subsequently,the solver constructed by this algorithm is used to solve three-dimensional two-phase flow field of the dual burning rate solid rocket motor.The whole structure of the three-dimensional flow field in solid rocket motor can be successfully obtained.%采用代数多重网格方法，求解可压缩形式SIMPLE算法中的压力修正方程，在同位网格基础上应用有限体积法离散Navier-Stokes方程组，数值模拟双燃速星型药柱固体火箭发动机燃烧室喷管三维流场；通过在不同规模网格下与直接求解法和不完全LU分解BiCGStab方法对比，研究了代数多重网格方法在求解此类问题中的计算效率。计算结果对比表明，代数多重网格方法增加了固体火箭发动机三维流场的求解效率。随后，将该算法构建的求解器用于求解双燃速固体火箭发动机三维两相流场，能成功获取固体火箭发动机三维内流场的整体结构。
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