|
|
论文:2012,Vol:30,Issue(5):768-772 |
|
|
引用本文： |
|
|
李佳明, 范建, 胡颖, 胡春波. 航天发动机多孔壁面发汗冷却液膜特性研究[J]. 西北工业大学 |
|
|
Li Jiaming, Fan Jian, Hu Ying, Hu Chunbo. Exploring Characteristics of Transpiration Cooling Liquid Film on Porous Wall of Rocket Engine[J]. Northwestern polytechnical university |
|
|
|
|
|
|
|
| 航天发动机多孔壁面发汗冷却液膜特性研究 |
|
| 李佳明1, 范建2, 胡颖1, 胡春波1 |
|
1. 西北工业大学, 陕西 西安 710072;
2. 北京宇航系统工程研究所, 北京 100076 |
| 摘要: |
| 为了研究多孔壁面发汗液膜冷却的特性,在对剪切气流驱动液滴变形和运动机理研究的基础上,采用步进电机控制液滴的体积,通过加热多孔壁面将液滴输送至连续剪切气流作用的实验风洞中,分析气流流速、壁面孔隙尺寸以及壁面温度对发汗液膜形状的影响。实验结果表明,剪切气流在推动发汗液膜向前伸展的同时也迫使其向两侧扩张,剪切气流速度超过某一临界速度时,液膜不再向两侧扩张;随着多孔壁面孔隙直径的增大,发汗液膜的面积不断增加,其增加程度逐渐降低;壁面温度越高,发汗液膜面积越小,完全蒸发耗时越少。 |
| 关键词:
冷却
液膜
多孔
火箭发动机
剪切流
|
|
| Exploring Characteristics of Transpiration Cooling Liquid Film on Porous Wall of Rocket Engine |
|
| Li Jiaming1, Fan Jian2, Hu Ying1, Hu Chunbo1 |
|
1. Northwestern Polytechnical University, Xi'an 710072, China;
2. Beijing Institute of Astronautical System Engineering, Beijing, 100076, China |
| Abstract: |
| To our knowledge, there is no paper in the open literature exploring the formation and characteristics ofliquid film in transpiration cooling.Based on the previous studies of the movement of the shear flow driven dropletson the surface of a solid body, we explore how transpiration cooling liquid film is formed on the surface.We use astepping motor to control the volume of a liquid droplet and to transport the liquid droplet to a wind tunnel with con-stant shear flow through heating the porous wall.Then we analyze the effects of flow velocity, the size of pore andthe temperature of porous wall on the formation of liquid film and its evaporation by the shear flow at differentspeeds.The experimental results, given in Figs.3 through 7, and their analysis show preliminarily that: (1) theshear flow not only pushes and extends the transpiration liquid film but also forces it to expand sideways; when theshear flow velocity exceeds a certain critical value, the liquid film stops its expansion; (2) the area of transpirationcooling liquid film increases with increasing diameter of pore on the porous wall, but after the diameter of the poreincreases to a certain degree, the increase in the liquid film area goes small; (3) the higher the wall temperature, the smaller are the liquid film area and the evaporation time. |
| Key words:
cooling
liquid films
porosity
rocket engines
shear flow
|
|
| 收稿日期: 2011-11-09
修回日期:
|
| DOI: |
| 基金项目: 国家自然科学基金(50976095)资助 |
| 通讯作者:
Email： |
| 作者简介: 李佳明(1984-)，西北工业大学博士研究生，主要从事航空宇航推进理论与工程的研究。
|
|
| 相关功能 |
|
|
|
|
| 作者相关文章 |
|
| 李佳明 在本刊中的所有文章 |
| 范建 在本刊中的所有文章 |
| 胡颖 在本刊中的所有文章 |
| 胡春波 在本刊中的所有文章 |
|
|
|
|
|
|
|
|
参考文献: |
|
|
[1] Schieb D J.Effects of Liquid Transpiration Cooling on Heat Transfer to the Diverging Region of a Porous-Walled Nozzle.Ph.D．Thesis,America,Alabama,Air University,1997
[2] Ludeke A,Haidn J,et al.Effusion Cooled CMC Rocket Combustion Chamber.AIAA-2005-3229
[3] Mayer W.TEKAN-Research on Cryogenic Rocket Engines at DLR Lampoldshausen.AIAA-2000-3219
[4] Steffen B,Georges C.Piah-Socar Fuel-Cooled Composite Materials Structure for Dual-Mode Ramjet and Liquid Rocket Engines．AIAA-2004-3653
[5] Meng L Y,Jiang P X,et al.Numerical Simulation of Fluid Flow and Heat Transfer in Transpiration Cooling.Journal of Engi-neering Thermophysics,2002,23(5): 593-595
[6] Jin S S,Jiang P X,et al.Investigation on the Transpiration Cooling of a Liquid Rocket Nozzle.Journal of Aerospace Power,2008,23(7):1334-1340
[7] Fan J,Wilson M,et al.Displacement of Liquid Droplets on a Surface by a Shearing Air Flow.Journal of Computational Infor-mation Systems,2001,356: 286-292 |
|
|
|
|
|
|
|
