高过载下长尾喷管整体热结构传热数值模拟  

Numerical Simulation for Thermal Structure of Tail-pipe Nozzle under High Overload

作　　者：高峰[1] 王建辉[2] 肖红雨[1] 

机构地区：[1]空军工程大学防空反导学院,西安710038 [2]空军工程大学理学院,西安710038

出　　处：《弹箭与制导学报》2014年第4期111-114,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中采用欧拉-拉格朗日两相流模型对不同过载及颗粒直径条件下的喷管内流场进行数值模拟。在此基础上,充分考虑了三种传热方式以及喷管内部各区域换热的特点,在耦合颗粒相传热后,对喷管三维整体的热结构进行了温度场计算分析。从喷管全域温度场分布情况可以看出,喷管内壁面温度梯度变化非常大;有颗粒相加入时长尾段后部的燃气温度以及喷管相同位置等值线区域的温度明显高于纯气相条件下的温度,但是热防护层的温度梯度下降很大;过载以及粒径的变化对喷管辐射传热的影响比较大。Numerical simulation was made on flow field inside nozzle with Euler-Lagrange two-phase flow model. Different overload and par- ticle＇ s diameter were considered. On the basis of calculation, temperature field of 31） thermal structure of the whole nozzle was analyzed with consideration of three heat transfer styles and heat transfer characteristics of each region of the nozzle. The global temperature of the nozzle shows that temperature gradient of inner wall of the nozzle is significant, with particles added, the gas temperature at the rear part of the nozzle is much higher than that without particle, while the temperature gradient descent occurs in thermal protection layer, the particle diameter has a great impact on radiation heat transfer in the nozzle.

关 键 词：高过载 长尾喷管 传热 数值模拟 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]