航空内燃发动机热管换热器的应用研究
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摘要
随着我国国民经济的发展和国防建设的需要,对轻型飞机的需求越来越大,对轻型飞机发动机的技术和性能要求也越来越高。车用发动机经过长期的发展和不断创新,其冷却系统尤其是换热器技术已经基本完善成熟,但航空发动机不同于车用发动机,其主要在高空运行,高空工况的复杂性和恶劣性是车用发动机无法比拟的。航空发动机换热器作为冷却传热的重要设备,在恶劣条件下,其散热性能的好坏直接影响发动机的散热效果及其动力性、经济性和可靠性,所以对航空发动机换热器的研究日益得到重视。
目前航空发动机换热器主要有管片式和管带式两种,所采用的换热方式也是传统的风冷和水冷。在高空进行风冷换热受到气压低,换热量小的制约,水冷又会带来质量的增加。考虑到热管和热管散热技术的特点,将热管应用于航空发动机换热器进行辐射换热不失为一种有意义的探索。
本文根据传热学理论,通过对热管换热器设计计算方法的归纳与总结,在增加辐射换热计算方法后,运用VB语言编制了热管辐射式换热器的设计计算程序,实现了热管辐射式换热器的程序化设计。
本文针对航空发动机换热器设计要求,以及无人机的性能参数,首先分析了热管工作液体和管壳材料的选择,然后利用热管换热器设计计算程序分析了包括换热面积、肋片参数、热管间距、等效热沉温度、冷却水温度、飞行速度等在内的多种内外参数对热管式换热器性能的影响,根据飞机运行的起飞工况和续航工况以及换热肋面的换热特点,通过模拟无人机运行的极限条件,最终给出本文所探索的热管辐射式换热器在匹配发动机换热器工作要求条件下的换热面积以及不同工况下换热面积的调节策略和较为合理的肋片结构参数与布置方式。
With the development of nation economy and the increasing needs of national defense, the demand for both high quantity of light aircraft and high quality of its technology and capability is increasing. The cooling system, especially the heat exchanger of engine used in vehicle has being improved and perfected, with the long time development and continuous innovation. Different from vehicle engines, aeroengine is required of ability to deal with complex and harsh situation in high altitude, which is uncomparible unparallel by engines of vehicle. As an important equipment of cooling and heat transfer, the stability of heat exchanger will directly affect the cooling capacity of aeroengine, and its mobility, efficiency and viability. As a result, research and development of aeroengine attracts increasing attention.
At present, there are two catagories of heat exchanger of engine, fin-tube and strip-tube. And there are two traditional ways of heat exchanging, air-cooling and water-cooling. In high altitude, air-cooling method is constrained by low air pressure and small capacity of heat exchange, however water-cooling increases mass. Concerning the characteristic of heat pipe and its heat radiation technology, it is a significant exploration to apply heat pipe to heat exchanger of aeroengine and to use method of radiational heat exchange.
In this paper, based on theory of heat transfer and the research of heat pipe exchanger design, with calculation of raidational heat exchange, by using VB language to formulate calculation procecures of design of radiational heat pipe, we realize programmed design of raidational heat exchanger.
According to the design requirement of aeroengine's heat exchanger, and performance parameter of unmanned aerial vehicle, this article analyzes the heat pipe working fluid and the choice of material, and utilizes calculation program of heat pipe exchanger to ananlyse the influence of heat transfer area, fin parameters, heat pipe spacing, space temperature, cooling water temperature, flight speed. Based on condition of takeoff and endurance of aeroplane, and heat exchanging charisteristics of fin surface, through a unmanned aerial vehicle operation in the extreme conditions, this article finally finds out area of heat exchanging, its adjust strategy under different condition, reasonable parameters of fin surface structure, and also the way of settlement.
目前航空发动机换热器主要有管片式和管带式两种,所采用的换热方式也是传统的风冷和水冷。在高空进行风冷换热受到气压低,换热量小的制约,水冷又会带来质量的增加。考虑到热管和热管散热技术的特点,将热管应用于航空发动机换热器进行辐射换热不失为一种有意义的探索。
本文根据传热学理论,通过对热管换热器设计计算方法的归纳与总结,在增加辐射换热计算方法后,运用VB语言编制了热管辐射式换热器的设计计算程序,实现了热管辐射式换热器的程序化设计。
本文针对航空发动机换热器设计要求,以及无人机的性能参数,首先分析了热管工作液体和管壳材料的选择,然后利用热管换热器设计计算程序分析了包括换热面积、肋片参数、热管间距、等效热沉温度、冷却水温度、飞行速度等在内的多种内外参数对热管式换热器性能的影响,根据飞机运行的起飞工况和续航工况以及换热肋面的换热特点,通过模拟无人机运行的极限条件,最终给出本文所探索的热管辐射式换热器在匹配发动机换热器工作要求条件下的换热面积以及不同工况下换热面积的调节策略和较为合理的肋片结构参数与布置方式。
With the development of nation economy and the increasing needs of national defense, the demand for both high quantity of light aircraft and high quality of its technology and capability is increasing. The cooling system, especially the heat exchanger of engine used in vehicle has being improved and perfected, with the long time development and continuous innovation. Different from vehicle engines, aeroengine is required of ability to deal with complex and harsh situation in high altitude, which is uncomparible unparallel by engines of vehicle. As an important equipment of cooling and heat transfer, the stability of heat exchanger will directly affect the cooling capacity of aeroengine, and its mobility, efficiency and viability. As a result, research and development of aeroengine attracts increasing attention.
At present, there are two catagories of heat exchanger of engine, fin-tube and strip-tube. And there are two traditional ways of heat exchanging, air-cooling and water-cooling. In high altitude, air-cooling method is constrained by low air pressure and small capacity of heat exchange, however water-cooling increases mass. Concerning the characteristic of heat pipe and its heat radiation technology, it is a significant exploration to apply heat pipe to heat exchanger of aeroengine and to use method of radiational heat exchange.
In this paper, based on theory of heat transfer and the research of heat pipe exchanger design, with calculation of raidational heat exchange, by using VB language to formulate calculation procecures of design of radiational heat pipe, we realize programmed design of raidational heat exchanger.
According to the design requirement of aeroengine's heat exchanger, and performance parameter of unmanned aerial vehicle, this article analyzes the heat pipe working fluid and the choice of material, and utilizes calculation program of heat pipe exchanger to ananlyse the influence of heat transfer area, fin parameters, heat pipe spacing, space temperature, cooling water temperature, flight speed. Based on condition of takeoff and endurance of aeroplane, and heat exchanging charisteristics of fin surface, through a unmanned aerial vehicle operation in the extreme conditions, this article finally finds out area of heat exchanging, its adjust strategy under different condition, reasonable parameters of fin surface structure, and also the way of settlement.
引文
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[3]王晓芳.铝散热器在汽车上的应用[J].机械工程师,2003.3：64-65
[4]郝旭辉.铜硬钎焊热交换器的性能特点分析[J].汽车技术,2003.11：34-37
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[11]H.F.Smimov, B.V.Kosoy. Refrigerating heat pipes[J]. Applied Thermal Engineering,2001. 21(6):631-641
[12]庄俊,张红.2010年热管技术展望.化工机械,1998.25(1)
[13]黄问盈.热管换热器设计基础[M].北京：中国铁道出版社,1995
[14]张力.中冷器技术与柴油机的发展.北京丰凯换热器有限责任公司.1999
[15]LeonardL, Vasiliev. Heat pipe fin modern heat exchangers [J]. Applied Thermal Engineering,2005.25:1-19
[16]秦娜.热管及其主要应用领域的研究[J].制冷与空调,2005.19(2)：79-81
[17]庄俊,张红.热管技术及其工程应用[M].北京：化学工业出版社,2000.6：201-202
[18]邵兴国,范含林,苗建印等.热管技术在航天领域应用和发展前景.第十届全国热管会议论文集.贵阳.2006：276-285
[19]Furukawam..Design and Off-Design Performance Calculations of Space Radiators [J].Journal of Spacecraft,1981,18(6):515-525.
[20]Ernst Messerschmid.Reinhold Bertrand Space Station:Systems and Utilization[M].Sprmger-Verlag Borlin H ridel—berg.1999.
[21]Toddwm,Jerrywb.Modeling and Performance of a Flat Plate Heat Pipe Fin Space Radiator[M].AIAA 34 Thermophysics Conference,2000.
[22]李明海,任建勋,梁新刚等.管肋式辐射器排热特性的数值分析与优化设计[J].工程热物理学报.2002,23(1)：88-90.
[23]张宁莉.液体回路—热管混合式辐射器的研究[D].北京：中国空间技术研究院硕十学位论文,2006.
[24]徐丽.正交热管网络辐射器的优化设计[D].北京：中国空间技术研究院硕士学位论文,1999.
[25]余小章.热管辐射器热分析[J].南京航空航天大学学报.1995,27(2)：180-185
[26]任德鹏,贾阳,刘强.肋片参数对辐射器散热性能的影响研究[J].中国空间科学技术.2007,8(4)
[27]华诚生.热管辐射器设计、试验及其在通信广播卫星上的应用[J].航天器工程.1997,6(1,2)
[28]杨世铭,陶文铨.传热学[M].北京：高等教育出版社,1998
[29]张玉中.高功率密度柴油机及其关键技术[J].车用发动机.2004(3)：5-7
[30]Rudiger Demark, Michael Groddeck, Georg Ruetz. Die neue Dieselmotoren- Baureihe 890 von MTU[J]. MTZ,2006(2):80-86
[31]郭振贤,刘仁涛.热管换热器应用现状及其制约因素[J].应用能源技术,2002(4)：32-33
[32]苏俊林,吴淑美,郝玉福.导热姆热管在汽车上的应用[J].吉林工业大学学报,1990(2)：35-38
[33]袁胜利.利用汽车废气取暖的热管换热器[J].节能,1991(11)：35-36
[34]张国正.车用余热热管暖风机的研究[D].洛阳：河南科技大学硕士论文,2003
[35]黎长青,彭忆强,黎薇等.热管技术在增压内燃机中的应用.西华大学学报：自然科学版(增刊),2007：157-159
[36]王春强.热管技术在增压内燃机中的应用[D].南宁：西大学硕士论文,2004
[37]王凯.热管换热器在中冷器上的应用研究[D].北京：北京交通大学,2010.1
[38]刘晓丽.发动机热管式中冷器热力性能优化设计研究[D].北京：北京交通大学,2010.7
[39]郭冬冬.活塞式航空发动机冷却系统性能仿真与设计[D].北京：北京交通大学,2008.7：13
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