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本文中对固体火箭喷管颗粒尺寸分级的两相跨音速流场作了计算.气相控制方程采用隐式近似因子分解法求解,尺寸分级的颗粒控制方程采用特征线求解,然后,二者进行充分的耦合,可以获得固体火箭发动机含有任意颗粒质量分数和不同颗粒尺寸时轴对称喷管跨音速流场的参数分布.文中讨论了不同颗粒半径和质量分数对流场的影响,对单一颗粒尺寸和颗粒尺寸分级的参数进行了比较.两相耦合计算的迭代收敛速度取决于气相,本文中气相方程求解的格式除部分边界外是隐式的,CFL数可取至6左右,收敛速度快.特别是对颗粒尺寸分级的计算,得益更大,其得益的倍数为颗粒的分级数.
In this paper, two-phase transonic flow field is calculated for particle size fractionation of solid rocket nozzle.The gas-phase control equation is solved by implicit approximation factorization method, and the particle grading equations for size fractionation are solved by characteristic line, and then the two are sufficiently , The parameter distribution of the transonic flow field in the axisymmetric nozzle can be obtained when the solid rocket motor contains arbitrary particle mass fraction and different particle size.The effects of different particle radius and mass fraction on the flow field are discussed, Particle size grading parameters are compared.The iterative convergence speed of two-phase coupling calculation depends on the gas phase.In this paper, the format of the gas phase equation is implicit except part of the boundary, the CFL number can be around 6, and the convergence speed is fast Grading the particle size calculation, greater benefit, the multiple of the benefits for the classification of particles.