火箭发动机平衡流与非平衡流模拟研究  

Simulation Research of Equilibrium Flow and Non-equilibrium Flow in Rocket Motors

作　　者：刘仔[1] 李艳臣 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150001 [2]上海卫星装备研究所,上海200240

出　　处：《弹箭与制导学报》2015年第4期97-100,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中通过数值模拟研究平衡流与非平衡流的差异和适用情况,为两相流数值模拟中选择合理的计算模型提供相应的参考。采用高雷诺数条件下的k-ε湍流模型、双流体模型以及全流速SIMPLE方法分别对发动机内的两相平衡流与非平衡流进行模拟研究。计算结果表明,平衡流与非平衡流计算得到的两相流场在喷管的扩张段存在差异,且差异随着膨胀比的增加而更加明显,因此当喷管扩张比较大时按非平衡流计算更准确。To provide corresponding reference for choosing reasonable calculation model in numerical simulation of two-phase flow,the difference and suitable situation of equilibrium flow and non-equilibrium flow were studied through numerical simulation. The k-ε turbulence model under high Reynolds number,two-fluid model and full-speed SIMPLE method were used to simulate equilibrium flow and nonequilibrium flow in solid rocket motors. Calculation results show that the difference existing in the expansion nozzle segment,and the difference is more obvious with increase of expansion ratio. We can conclude that the simulation result of two-phase is more accurate when the expansion ratio of nozzle is relatively large.

关 键 词：k-ε湍流模型 双流体模型 平衡流 非平衡流 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]