Application of algebraic multigrid method in numerical simulation of solid rocket 3D flow field

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 combustion 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) algorithm 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-dimensional 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.