期刊文献+

低气压高空膜式水蒸发循环冷却试验研究

Experimental study on water membrane evaporator circulation cooling system in high altitude area
下载PDF
导出
摘要 为研究膜式水蒸发(WME)循环冷却技术在低气压高空环境中的应用可能,搭建以去离子水为工质的WME循环冷却系统试验平台。试验结果表明:系统在低于10 kPa的低气压环境下可以实现将55—70℃的热水降温至45—55℃的冷水,膜组件进出口温差最大达到16.8℃,制冷功率达到4 kW,膜组件热效率高于80%;系统具有一定自适应能力,随着加热功率的提高,制冷量也相应提高;系统结构简单紧凑、体积小、重量轻、易实现,在低气压高空温控应用中有着广阔前景。 In order to study the possible application of water membrane evaporation(WME)circulating cooling technology in the high altitude area where is under lower atmospheric pressure condition,a WME circulating cooling system experimental platform was built using deionized water as the working fluid.The results show that the system can cool down the hot water at a range from 55℃to 70℃towards cold water at a range from 45℃to 55℃in a low pressure surroundings lower than 10 kPa.The maximum temperature difference between the inlet and outlet of the membrane module reaches 16.8℃and the cooling power reaches 4 kW,and the thermal efficiency of the membrane module is higher than 80%.The system has a self-regulation capability:the cooling capacity increases with the increase of heating power.In summary,the system has the advantage of simple and compact structure,small size and light weight,which has broad prospects in the application of temperature control of electronic equipment in the high altitude area.
作者 杨宝山 张文瑞 朱建炳 于凯盈 于锟锟 Yang Baoshan;Zhang Wenrui;Zhu Jianbing;Yu Kaiying;Yu Kunkun(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,China)
出处 《低温工程》 CAS CSCD 北大核心 2021年第2期76-82,共7页 Cryogenics
关键词 低气压高空环境 膜式水蒸发器 循环冷却 热效率 试验研究 low pressure atmosphere water membrane evaporator circulation cooling thermal efficiency experimental study
  • 相关文献

参考文献2

二级参考文献68

  • 1王华彬,韩杰才,杜善义.自蔓延高温合成技术应用的新进展[J].功能材料,1997,28(2):115-121. 被引量:13
  • 2[3]PURINTON D. Multioclave supersonic radome[C]. Proceedings of the 16th symposium on electromagnetic windows. Atlanta, 1982. 218-223.
  • 3童秉纲,孔祥言,邓国华.气体动力学[M].北京:高等教育出版社,1989.241~285.
  • 4Oswatitsch K.Similarity laws for hypersonic flow[J].Royal Institute of Technology,1950,2:249-264.
  • 5Kliche D,Mundt C H,Hirschel E H.The hypersonic Mach number independence principle in the case of viscous flow[J].Shock Waves,2011,21(4):307-314.
  • 6Anderson J D.Hypersonic and high temperature gas dynamics[M].New York:McGraw-Hill Book Company,1989.
  • 7Bertin J J,Cummings R M.Fifty years of hypersonics:where we' ve been,where we' re going[J].Progress in Aerospace Sciences,2003,39(6-7):511-536.
  • 8Bertin J J,Cummings R M.Critical hypersonic aerothermodynamic phenomena[J].Annual Review of Fluid Mechanics,2006,38:129-157.
  • 9Reshotko E,Tumin A.The blunt body paradox-a case for transient growth[M]// Fasel H F,Saric W S.Laminar-turbulent transition.Heidelberg:Springer,2000:403-408.
  • 10Hirschel E H,Weiland C.Selected aerothermodynamic design problems of hypersonic flight vehicles[M].Heidelberg:Springer-Verlag,2009.

共引文献70

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部