NACA0021和NACA4822翼型肋通道中环境空气流动传热特性的实验研究  

Experimental Study on Flow and Heat Transfer Characteristics of Ambient Air in NACA0021 and NACA4822 Airfoil⁃Fin Channels

作　　者：李勇 张迎春[3] 付虞 周棋润 赵雨菲 杨森杰 马素霞 LI Yong;ZHANG Yingchun;FU Yu;ZHOU Qirun;ZHAO Yufei;YANG Senjie;MA Suxia(College of Electrical and Power Engineering,Taiyuan University of Technology,Taiyuan 030024,P.R.China;Key Laboratory of Cleaner Intelligent Control on Coal&Electricity,Ministry of Education,Taiyuan 030024,P.R.China;School of Energy and Power Engineering,North University of China,Taiyuan 030051,P.R.China)

机构地区：[1]太原理工大学电气与动力工程学院,太原030024 [2]煤电清洁控制教育部重点实验室,太原030024 [3]中北大学能源与动力工程学院,太原030051

出　　处：《应用数学和力学》2024年第5期594-605,共12页Applied Mathematics and Mechanics

基　　金：山西省基础研究计划青年基金(202203021212263);中国博士后科学基金(面上项目)(2023M732569);山西省回国留学人员科研资助项目(2023-055;2023-143);教育部“春晖计划”合作科研项目(202200075)。

摘　　要：针对超燃冲压发动机在更高Mach数飞行时,主动再生冷却技术面临换热能力不足的瓶颈问题,拟利用翼型肋加强再生冷却通道的传热性能.为了从原理上验证翼型肋通道的强化传热效果,搭建了环境空气在NACA0021对称翼型肋和NACA4822非对称翼型肋通道(横截面尺寸50 mm×50 mm)中的流动传热实验测试平台,基于稳态液晶技术得到受热表面的Nusselt数.通过实验研究发现:NACA0021对称翼型肋通道和NACA4822非对称翼型肋通道的传热强度分别被提升了0.17%~17.1%和18.4%~52.1%,50 m^(3)/h流量下的PEC(performance evaluation criteri-on)分别为1.04和1.24;大流量条件下,NACA4822非对称翼型肋通道可强化中间受热面的传热性能;翼型肋通道中的流动压降也会相应增大,其中NACA4822翼型肋通道中的压降最大,翼型肋的非对称性使得流动湍流强度不断积累造成下游压降存在明显升高.该研究将有助于进一步开展翼型肋通道内超临界流体的流动传热特性研究,拓宽超燃冲压发动机主动再生冷却技术的应用温区.The active regenerative cooling technology faces the bottleneck problem of insufficient heat transfer capacity when the scramjet flies at a higher Mach number.It is proposed to strengthen the heat transfer per-formance of the regenerative cooling channel with airfoil-fins.To verify the enhanced heat transfer effect of the airfoil-fin channel in principle,an experimental test platform for flow and heat transfer of ambient air in NA-CA0021 symmetrical airfoil-fin channels and NACA4822 asymmetric airfoil-fin channels(with cross-section sizes of 50 mm×50 mm)was built.The Nusselt number of the heated surface was obtained based on the steady-state liquid crystal technique.The results show that,the heat transfer intensities of NACA0021 symmetrical air-foil-fin channels and NACA4822 asymmetric airfoil-fin channels improve by 0.17%~17.1%and 18.4%~52.1%,respectively.Correspondingly,PECs are 1.04 and 1.24,respectively,with the volume flow of ambient air at 50 m^(3)/h.The NACA4822 asymmetric airfoil-fin channel can enhance the heat transfer performance of the middle heating surface under the condition of a large flow rate.The flow pressure drop in the airfoil-fin channels also increases correspondingly,where the pressure drop in the NACA4822 airfoil-fin channel is the largest.The a-symmetry of the airfoil-fin causes the continuous accumulation of flow turbulence intensity,resulting in a signif-icant increase in the downstream pressure drop.The work is helpful for further research on the flow and heat transfer characteristics of supercritical fluids in airfoil-fin channels,and broadens the application temperature range of the active regenerative cooling technology for scramjets.

关 键 词：超燃冲压发动机 翼型肋通道 NUSSELT数 压力损失 

分 类 号：O35[理学—流体力学] V19[理学—力学]