高温热管性能分析与试验

doi:10.7527/S1000-6893.2016.0165

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高温热管性能分析与试验

牛涛^1,2, 张艳苓^1,2,3, 侯红亮^1,2,3, 王耀奇^1,2,3, 何铎⁴

1. 北京航空制造工程研究所, 北京 100024;
2. 塑性成形技术航空科技重点实验室, 北京 100024;
3. 数字化塑性成形技术及装备北京市重点实验室, 北京 100024;
4. 北京科技大学材料科学与工程学院, 北京 100083

收稿日期:2016-05-05 修回日期:2016-05-26 出版日期:2017-01-10 发布日期:2016-06-07
通讯作者: 侯红亮,Tel.:010-85701237,E-mail:hou_hl@163.com E-mail:hou_hl@163.com
作者简介:牛涛,男,硕士,工程师。主要研究方向:热管技术、轻合金材料成形与连接技术。Tel.:010-85701237,E-mail:niutaoplane@163.com;侯红亮,男,博士,研究员,博士生导师。主要研究方向:钛基复合材料技术、轻合金材料成形与连接技术。Tel.:010-85701237,E-mail:hou_hl@163.com
基金资助:
国家重点基础研究发展计划（2011CB012803）；航空科学基金（2013ZE25007）

Properties of high-temperature heat pipe and its experimental

NIU Tao^1,2, ZHANG Yanling^1,2,3, HOU Hongliang^1,2,3, WANG Yaoqi^1,2,3, HE Duo⁴

1. Beijing Aeronautical Manufacturing Technology Research Institute, Beijing 100024, China;
2. Aeronautical Key Laboratory for Plastic Forming Technology, Beijing 100024, China;
3. Beijing Key Laboratory of Digital Forming Technology and Equipment, Beijing 100024, China;
4. School of Materials Science and Engineering, University of Science and Technology Beijing, Beijing 100083, China

Received:2016-05-05 Revised:2016-05-26 Online:2017-01-10 Published:2016-06-07
Supported by:
National Basic Research Program of China (2011CB012803);Aeronautical Science Foundation of China (2013ZE25007)

摘要/Abstract

摘要：

设计并制备了钠工质、高温合金管壳的丝网型高温热管，测试并分析了在辐射和自然对流散热条件下不同加热功率和不同倾角对热管启动特性和稳态工作后等温性能的影响。结果表明，钠高温热管在不同倾角下都可顺利启动，而且随着加热功率的增加，钠高温热管启动时间越短，但倾角对启动时间影响不大。在倒置45°和倒置90°倾角时，在较大功率下热管的蒸发段出现温度激增现象，分析认为是由于丝网吸液芯毛细力不足导致蒸发段出现工质干涸造成的，说明已经达到了热管的毛细极限。

关键词: 高温热管, 钠, 启动特性, 传热性能, 翼面前缘

Abstract:

High-temperature heat pipe (HTHP) with sodium as medium, superalloy pipe as container wall and silk screen as wick is designed and prepared. The characteristic of start-up and the isotherm capacity after steady working is tested and studied at different heating power and obliquity with the cooling of eradiation and convection. The results show that all of the HTHPs could be started up successfully at different obliquity, and the start-up time is shorter with higher heating power, but the effect of obliquity on the start-up time is small. There is a sharp increase of temperature on the evaporation section at the obliquity of inverted 45° and inverted 90° with a higher heating power. Analysis suggests that it is due to the drying up of the sodium medium on the evaporation section resulting from the insufficient ability of the silk wick's capillary force, which means the capacity of heat transferring has reached the capillary limit.

Key words: high-temperature heat pipe, sodium, characteristic of start-up, isotherm capacity, leading edge

中图分类号:

牛涛, 张艳苓, 侯红亮, 王耀奇, 何铎. 高温热管性能分析与试验[J]. 航空学报, 2016, 37(S1): 59-65.

NIU Tao, ZHANG Yanling, HOU Hongliang, WANG Yaoqi, HE Duo. Properties of high-temperature heat pipe and its experimental[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(S1): 59-65.

参考文献

[1] 陈连忠, 欧东斌. 高温热管在热防护中应用初探[J]. 实验流体力学, 2010, 24(1):51-54. CHEN L Z, OU D B. Elementary research on the application of high temperature heat-pipe to the thermal protection[J]. Journal of Experiments in Fluid Mechanics,2010, 24(1):51-54 (in Chinese).
[2] SILVERSTEIN C C. A feasibility study of heat-pipe-cooled leading edges for hypersonic cruise aircraft[R]. Washington, D.C.:NASA, 1971.
[3] CUMURDU C J. Analysis and radiant heating tests of a heat pipe cooled leading edge[R]. Washington, D.C.:NASA, 1977.
[4] GLASS D E, MERRIGAN M A, SENA J T. Fabrication and testing of Mo-Re heat pipes[R]. Washington, D.C.:NASA, 1998.
[5] MDC. Design, fabrication, testing and delivery of Shuttle heat pipe leading edge test modules[R]. Washington, D.C.:NASA,1973.
[6] CAMARDA C J. Analysis and radiant heating tests of a heat-pipe-cooled leading edge[R]. Washington, D.C.:NASA,1977.
[7] BOMAN B, ELIAS T. Tests on a sodium/Hastelloy X wing leading edge heat pipe for hypersonic vehicles[C]//5th Joint Thermophysics and Heat Transfer Conference. 1990.
[8] DICKINSON T J, BOWMAN W J, STOYANOF M. Performance of three liquid metal heat pipes during a space shuttle flight:AIAA-1997-2540[R]. Reston:AIAA,1997.
[9] QU W. Progress works of high and super high temperature heat pipes[M]//Developments of Heat Transfer. 2011:503-522.
[10] 曲伟, 王焕光, 段彦军. 高温及超高温热管的启动特性和传热极限[J]. 工程热物理学报, 2011, 32(8):1345-1348. QU W, WANG H G, DUAN Y J. Startup characteristics and heat transfer limits of high and super high temperature heat pipes[J]. Journal of Engineering Thermophysics, 2011, 32(8):1345-1348 (in Chinese).
[11] 冯踏青. 液态金属高温热管的理论和试验研究[D]. 杭州:浙江大学, 1998:88-111. FENG T Q. Theoretical and experimental research on liquid metal high temperature heat pipe[D]. Hangzhou:Zhejiang University, 1998:88-111 (in Chinese).
[12] 捷曼尔M.G, 胡亚才, 冯踏青, 等. 钠钾合金高温热管性能试验研究[J]. 浙江大学学报(工学版), 1999, 33(4):414-417. GAMAL M G, HU Y C, FENG T Q, et al. Analysis on the properties of NaK alloy high temperature heat pipe and its experimental study[J]. Journal of Zhejiang University(Engineering Science), 1999, 33(4):414-417(in Chinese).
[13] 刘冬环, 郑小平, 王飞, 等. 内置高温热管热防护结构的传热防热机理[J]. 清华大学学报(自然科学版), 2010, 50(7):1094-1098. LIU D H, ZHENG X P, WANG F, et al. Heat conduction and thermal protection mechanism of heat pipe cooled thermal protection structures[J]. Journal of Tsinghua University(Science & Technology), 2010, 50(7):1094-1098 (in Chinese).
[14] 刘冬环, 郑小平, 黄拳章. C/C复合材料与高温合金GH600之间高温接触热阻的试验研究[J]. 航空学报, 2010, 31(11):2189-2194. LIU D H, ZHENG X P, HUANG Q Z. Experimental investigation of high-temperature thermal contact resistance between C/C composite material and superalloy GH600[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(11):2189-2194 (in Chinese).
[15] 谢宗蕻, 孙俊峰. 高超声速飞行器翼面前缘半主动金属热防护系统设计与分析[J]. 航天器环境工程, 2013, 30(1):1-7. XIE Z H, SUN J F. Design and analysis of semi-active thermal protection system for the leading edges of hypersonic vehicles[J]. Spacecraft Environment Engineering, 2013, 30(1):1-7 (in Chinese).

E-mail：hkxb@buaa.edu.cn

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高温热管性能分析与试验

Properties of high-temperature heat pipe and its experimental

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