CAJ | 학술논문

为了计算高速旋转过载下固体火箭发动机喷管受热状态，本文采用流固热耦合计算方法对喷管进行了仿真。计算结果中温度云图与受热密度分布均表明在高速旋转条件下，随着转速的不断增加以及发动机工作时间的延续，高温燃气对喷管内壁面热交换的总热流密度逐渐降低，发动机喷管喉部前端位置总热流密度最大，换热最为强烈。由于高速旋转导致的强旋流动使喷管内燃气所具有的部分动能逐渐耗散并转变为热能，壁面的传热加强。
위료계산고속선전과재하고체화전발동궤분관수열상태，본문채용류고열우합계산방법대분관진행료방진。계산결과중온도운도여수열밀도분포균표명재고속선전조건하，수착전속적불단증가이급발동궤공작시간적연속，고온연기대분관내벽면열교환적총열류밀도축점강저，발동궤분관후부전단위치총열류밀도최대，환열최위강렬。유우고속선전도치적강선류동사분관내연기소구유적부분동능축점모산병전변위열능，벽면적전열가강。
To calculate the heated state of a rocket motor nozzle under the condition of different ro-tate speed, the fluid-solid heat coupling model is adopted.The calculation results show that as a continua-tion of the engine work time, total heat transfer of the wall heat flux density gradually reduces in the noz-zle, it reaches the most in the front of engine nozzle throat, and the heat transfer is the strongest.The strong spiral flow due to high speed rotating makes the part of the gas kinetic energy in nozzle gradually dissipate into heat energy, leads to the increased heat transfer of wall.