关键词: 收敛扩散喷管;跨音速流;二相流;计算方法;固体火箭发动机;计算

Abstract: In this paper, the time-dependent method is applied to the numerical computation of transonic nozzle flows by using of conservation and nonconservation governing equations.The computation of the JPL nozzle shows that the convergent rate of the nonconservation equations is more than twice as much as that of the conservation equations with the same precision,and the computational and experimental results are fairly identical.When the corrected dashpot method is applied, the convergent rate is seven times higher than that of the corresponding time-dependent method with the same precision.The convergent rate varies widely with the damping factor K and the time interval r. Finally, the direct optimization technique is applied to the study of the effects of nozzle inlet and throat geometry on the performance of solid rocket motors. Some conclusions are drawn from the experimental results.

Key words: Convergent divergent nozzle;Transonic flow;Two-Phase flow;Calculation method;Solid Rocket engine;Calculation