脉冲爆轰发动机管壁传热特性的数值研究  

Numerical Study on Heat-transfer Characteristics of Pulse Detonation Tube

作　　者：倪晓冬 翁春生[1] 白桥栋[1] NI Xiaodong;WENG Chunsheng;BAI Qiaodong(National Key Laboratory of Transient Physics,Nanjing University of Science&Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《弹道学报》2018年第3期60-66,共7页Journal of Ballistics

基　　金：国防预研基金项目(61426040201162604002)

摘　　要：为了探究爆轰过程中燃烧室管壁的传热特性,采用CE/SE方法和有限差分法分别对气液两相脉冲爆轰发动机(PDE)内流场及燃烧室管壁的传热问题进行了数值计算;运用能量平衡法解决了内流场与管壁传热之间的耦合传热问题。计算结果表明,对于燃烧室内任一截面,爆轰波扫过或膨胀波到来时,对流换热强度大,内壁面温度上升快;单次爆轰时,爆轰波所在区域温度高达2 000 K,管壁靠近内壁面的区域径向上存在较大的温度梯度,靠近外壁面的区域温度几乎没有变化;当燃烧室管口压力恢复到环境压力时,从PDE头部到尾部,管壁内壁面温度逐渐升高,热量传递区域厚度逐渐增大。To explore the heat-transfer characteristics of pulse detonation tube during detonation process,the interior flow-field and heat-transfer process of gas-liquid two-phase pulse detonation engine(PDE)were calculated by the CE/SE method and the finite difference method.The problem of coupled heat-transfer was solved by the energy balance method.The calculated results show that the convective heat transfer is strong,and the temperature of inner wall rises fast where detonation wave or expansion wave is located.The maximum temperature of gas inside the combustion chamber is higher than 2 000 K in a single detonation process.The radial thermal gradient of the tube is large near the inner wall while the temperature of the tube near the outer wall does not change.When the combustor-outlet pressure returns to ambient pressure,both the temperature of the inner wall and the thickness of the heat-transfer part increase gradually from head to tail of PDE.

关 键 词：脉冲爆轰发动机 爆轰波 流场 传热 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]