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弹箭与制导学报 >

2014 , Vol. 34 >Issue 4: 111 - 114

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.04.010

火箭技术

高过载下长尾喷管整体热结构传热数值模拟

  • 高峰 ,
  • 王建辉 ,
  • 肖红雨
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  • 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

高峰(1965-),男,安徽凤阳人,副教授,研究方向:航空宇航推进理论与工程。

收稿日期: 2013-08-27

  网络出版日期: 2025-05-30

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

  • GAO Feng ,
  • WANG Jianhui ,
  • XIAO Hongyu
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  • 1 Air and Missile Defense College, Air Force Engineering University, Xi'an 710038, China
    2 Science College, Air Force Engineering University, Xi'an 710038, China

Received date: 2013-08-27

  Online published: 2025-05-30

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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。

关键词： 高过载; 长尾喷管; 传热; 数值模拟

本文引用格式

高峰 , 王建辉 , 肖红雨 . 高过载下长尾喷管整体热结构传热数值模拟[J]. 弹箭与制导学报, 2014 , 34(4) : 111 -114 . DOI: 10.15892/j.cnki.djzdxb.2014.04.010

Abstract

Numerical simulation was made on flow field inside nozzle with Euler-Lagrange two-phase flow model. Different overload and particle's diameter were considered. On the basis of calculation, temperature field of 3D 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.

Key words： high acceleration; tail pipe-nozzle; heat transfer; numerical simulation

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参考文献

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