高超声速溢流冷却实验研究

苑朝凯; 李进平; 陈宏; 姜宗林; 俞鸿儒

doi:10.6052/0459-1879-17-289

高超声速溢流冷却实验研究

doi: 10.6052/0459-1879-17-289

苑朝凯^1,2,*, ,,
李进平¹,
陈宏¹,
姜宗林^1,2,
俞鸿儒¹

¹中国科学院力学研究所高温气体动力学国家重点实验室,北京 100190
²中国科学院大学工程科学学院,北京 100049

基金项目: 国家自然科学基金资助项目(11602275, 11472280).

详细信息

作者简介:
苑朝凯,工程师,主要研究方向：高超声速热防护. E-mail: yuanck@imech.ac.cn

通讯作者:
苑朝凯

中图分类号: V211.7;
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出版历程
- 收稿日期: 2017-08-29
- 刊出日期: 2018-01-18

EXPERIMENTAL STUDY OF HYPERSONIC OVERFLOW COOLING

¹State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
²School of Engineering Sciences,University of Chinese Academy of Sciences, Beijing 100049, China

摘要

摘要: 高超声速溢流冷却是一种新型的飞行器热防护方法,基本思想为：在高热流区布置溢流孔,控制冷却液以溢流方式流出,之后通过飞行器表面摩阻作用展布为液膜,形成热缓冲层以降低飞行器表面热流. 目前,溢流冷却技术还处于探索阶段,实现工程应用前还需开展大量的实验验证和机理研究工作. 本文首次开展溢流冷却的实验研究工作,采用热流测量、液膜厚度测量及液膜流动特性观测技术,搭建了完善的溢流冷却风洞实验平台,对溢流冷却热防护性能和高超声速条件下液膜流动规律进行了初步研究. 研究表明：(1) 高超声速流场中通过溢流能够在飞行器表面形成液膜并有效隔离外部高温气流,可降低飞行器表面热流率;(2) 楔面上的液膜前缘流动是一个逐渐减速的过程,增加冷却液流量液膜厚度变化不明显,但液膜前缘运动速度增大;(3) 液膜层存在表面波,在时间和空间方向发生演化,导致液膜厚度的微弱扰动;(4) 液膜层存在横向展宽现象,即液膜层宽度大于溢流缝宽度. 原因是液膜层与流场边界层条件不匹配,存在压力梯度,迫使冷却液向低压区流动,从而展宽液膜层,并且流量越高,横向展宽现象越明显.
- 高超声速热防护 /
- 主动冷却 /
- 溢流冷却 /
- 液膜
Abstract: Hypersonic overflow cooling is a new type of aircraft thermal protection method. The basic idea is that the overflow hole is arranged in the high heat flux area, and the coolant poured out in an overflow way.The liquid film spreads through the aircraft surface friction forming a thermal buffer layer to reduce the surface heat flux. Now, the overflow cooling technology is still in the exploratory stage, and a large number of experimental verification and mechanism research work need to do. In this paper, wind tunnel experiment platform for overflow cooling was build, adopting the heat flux measurement, liquid film thickness measurement and liquid film motion observation technology. The feasibility of applying overflow cooling to hypersonic thermal protection was verified, and the characteristics of liquid film flow under hypersonic flow field were preliminary analyzed. Reserch results show that: (1) In hypersonic flow field, the liquid film can be formed on the vehicle surface , and effectively isolate the external high temperature air to reduce the surface heat flux; (2) On wedge surface, the leading velocity of the liquid film gradually decelerate. Increase coolant flow rate, the liquid film thickness change is not obvious, but the leading velocity of liquid film will increase; (3) Surface waves exist in liquid film, and evolve in time and space direction, which leads to slight perturbation of liquid film thickness; (4) There is a lateral expansion phenomenon in the liquid film layer, that is, the width of the liquid film is greater than that of the overflow hole. The reason is that the liquid film layer don’t match the flow field boundary condition, and there is pressure gradient, forcing the coolant to flow to low pressure area, thus broadening the liquid film layer.
- hypersonic thermal protection /
- active cooling /
- overflow cooling /
- liquid film

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