导弹舱室固体火箭发动机意外点火的喷雾降温数值模拟

为防止舰船导弹舱室内固体火箭发动机发生意外点火，避免出现火灾事故，对导弹舱室内固体火箭发动机意外点火的燃气流场进行数值模拟，并基于组分输运和DPM离散相喷雾模型对导弹舱室内的喷雾降温效率进行耦合计算。然后，通过改变喷嘴组合位置、喷嘴数量、喷雾强度、雾锥角和水温研究相关因素对导弹舱室喷雾降温效率的影响。结果显示：在喷雾降温作用下，导弹舱室内的温度快速下降，温度在3s内可下降至400K以下。但是，射流冲击区的降温却不理想，且导弹舱室的底板还需要特殊的热防护措施。同时，考虑到火源的随机性，喷嘴应尽可能均匀布置，数量不宜过少且雾锥角应较大，以提高降温效率。然而，当喷雾强度增大至一定程度后，若再继续增大，降温效率的提高却不明显。研究表明，采用所提喷雾降温数值模拟方法对导弹舱室内固体火箭发动机的意外点火情况进行降温和防控均有效可行。

Numerical Study of the Spray Cooling Process After Accidental Ignition of the Rocket Motor in Magazines

In this paper, the exhaust gas flow fields are simulated in the case of accidental ignition of the rocket motor within the magazine. Particularly, the component transport and the DPM are used to simulate the spray cooling process and the exhaust gas physical fields. Numerical simulation is conducted with dif- ferent influential factors such as the number, position, and water intensity of nozzles as well as the cone angle and temperature of the spray, and their respective effects on the cooling process are investigated. Re- sults show that the temperature in the magazine drops significantly after the spray cooling, which drops be- low 400 K within 3 seconds and slowly decreases afterwards. In contrast, the cooling effect in the imping- ing jet zone is not so ideal, so the magazine baseboard requires special thermal insulation. Also, consider- ing the randomness of the fire source, a substantial number of liquid nozzles, with large cone spray an- gles, should be evenly distributed in the magazine so that the cooling efficiency can be maximized. Final- ly, when the spray intensity reaches a certain level, its effect on the overall cooling efficiency becomes less obvious if it continues to enhance.