关键词: 固体火箭发动机;喷管;二相流;跨音速流;粒子谱

Abstract: 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.

Key words: Solid rocket engine;Nozzle;Two-phase flow;Transonic flow;Particle spectrum