高温热管性能分析与试验
收稿日期: 2016-05-05
修回日期: 2016-05-26
网络出版日期: 2016-06-07
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
Received date: 2016-05-05
Revised date: 2016-05-26
Online published: 2016-06-07
Supported by
National Basic Research Program of China (2011CB012803);Aeronautical Science Foundation of China (2013ZE25007)
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 . DOI: 10.7527/S1000-6893.2016.0165
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.
[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).
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