固体火箭喷管颗粒尺寸分级两相跨音速流场计算

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.

TWO-PHASE TRANSONIC CALCULATION OF SOLID ROCKET NOZZLE IN CONDITION OF PARTICLE SIZE GRADING

In this paper, we calculated two-phase transonic flow of solid rocket nozzle in condition of particle size grading. The gas-phase governing equations are solved by the implicit approximate factorization scheme.The particle-phase governing equations are solved by charateristic scheme.Then both are full co-upled.Finally, the parameter distributions of a transonic flow field of axisymmtric nozzle are obtained for solid rocket motor containing any particle mass fraction and different particle size. We also discussed the influence of different particle radius and mass fraction with flow field,and compared the flow field parameters possessing si- mple particle size with one possessing particle size grading. At present, explicit-time dependent method is used in the field calculation of two-phase nozzle generally in our paper.The solution form of gas-phase equations is implicit-time dependent,the CFL number may be taken to 6.Convergent rate is quick. The iteration convergent rate of two-phase calculation depends on gas-phase calculation.Consequently,computer time are greatly saved. Especially,it will obtain more benefit for the coupling of particle size grading. Generally, two-phase field calculation consumes more computer time. Hence its application scope is limited. Especially, it is more difficut for apply it when repeatedly swaping in optimization design of motor.Consequently , it possesses very greatly praticle engienering meaning to find two-phase field calculation method deducing greatly computer time.