各向异性复合材料平板气膜冷却特性实验和数值研究
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摘要
针对不同编织方式形成的复合材料平板气膜冷却开展了实验研究,利用红外热像仪测量了热侧壁面的温度场分布,分析了平板导热系数、吹风比、主流温度等参数对综合冷却效率的影响。在实验验证的基础上,进一步对单向增韧特点的复合材料进行数值模拟,分析了X、Y、Z三个方向导热系数对单孔气膜冷却壁面温度场分布和综合冷却效率的影响。结果表明:随着吹风比的升高,气膜综合冷却效率升高;随着主流温度的升高,气膜冷却效率降低;2.5D编织复合材料冷却效率最高,3D编织复合材料冷却效率最低。各向异性复合材料内部的温度梯度、传热量都与材料的导热系数特征有关,X方向和Z方向的导热系数增大,沿程综合冷却效率升高;而Y方向导热系数的增大对气膜冷却效率几乎没有影响。
Experimental studies were carried out on the film cooling of the composite plates formatted through different weaving modes.An infrared radiation camera was used to capture the temperature distributions on hot side wall,and the effects of thermal conductivity,blowing ratio,and mainstream temperature on the overall cooling effectiveness were analyzed.Numerical simulations on the anisotropic composite plates with a single film hole were further conducted to explore the individual influence of thermal conductivity along the X,Y,and Zdirections on the wall temperature distribution as well as the overall cooling effectiveness.Results show that the film cooling effectiveness increases with the enhancement of the blowing ratio and decreases with the increase of the main stream temperature.Among thethree anisotropic composite plates,2.5Dcomposite plate produces the highest film cooling effectiveness while 3Dcomposite plate gives the lowest cooling effectiveness.The increase of thermal conductivity along X and Zdirections can improve the film cooling efficiency while the increase of thermal conductivity along Ydirection has little influence on the film cooling efficiency.
Experimental studies were carried out on the film cooling of the composite plates formatted through different weaving modes.An infrared radiation camera was used to capture the temperature distributions on hot side wall,and the effects of thermal conductivity,blowing ratio,and mainstream temperature on the overall cooling effectiveness were analyzed.Numerical simulations on the anisotropic composite plates with a single film hole were further conducted to explore the individual influence of thermal conductivity along the X,Y,and Zdirections on the wall temperature distribution as well as the overall cooling effectiveness.Results show that the film cooling effectiveness increases with the enhancement of the blowing ratio and decreases with the increase of the main stream temperature.Among thethree anisotropic composite plates,2.5Dcomposite plate produces the highest film cooling effectiveness while 3Dcomposite plate gives the lowest cooling effectiveness.The increase of thermal conductivity along X and Zdirections can improve the film cooling efficiency while the increase of thermal conductivity along Ydirection has little influence on the film cooling efficiency.
引文
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[17]张建可.树脂基碳纤维复合材料的热物理性能之一——导热系数[J].中国空间科学技术,1987,7(3):55-60.ZHANG Jianke.The one of thermal physical properties of carbon fibre/epoxy—resin composites-thermal conductivity[J].Chinese Space Science and Technology,1987,7(3):55-60.(in Chinese)
[18]马青松,刘海韬,潘余,等.C/SiC复合材料在超燃冲压发动机中的应用研究进展[J].无机材料学报,2013,28(3):247-255.MA Qingsong,LIU Haitao,PAN Yu,et al.Research progress on the application of C/SiC composites in scramjet[J].Jouranl of Inorganic Materials,2013,28(3):247-255.(in Chinese)
[19]陈洁,熊翔,肖鹏.单向C/C复合材料导热系数的计算[J].炭素技术,2008,27(2):1-4.CHEN Jie,XIONG Xiang,XIAO Peng.Calculation of thermal conductivity coefficient in undirectional carbon/carbon composite[J].Carbon Techniques,2008,27(2):1-4.(in Chinese)
[2]刘捷,韩振兴,蒋洪德,等.不同复合角对平板气膜冷却特性影响的实验研究[J].工程热物理学报,2008,29(8):1311-1315.LIU Jie,HAN Zhenxing,JIANG Hongde,et al.Experimental research on flat plate film cooling effectiveness at different complex angles[J].Journal of Engineering Thermolhysics,2008,29(8):1311-1315.(in Chinese)
[3]GRISCH M,SCHULZ A,WITTING S.Adiabatic wall effectiveness measurement of film-cooling holes with expanded exits[J].Journal of Turomachinery,1998,120(3):549-556.
[4]张勃,吉洪湖,杨芳芳,等.多斜孔壁与机加环气膜冷却燃烧室的壁面换热特性数值研究[J].航空动力学报,2012,27(4):832-836.ZHANG Bo,JI Honghu,YANG Fangfang,et al.Numerical investigation of heat transfer characteristics of effusion cooling and machinery film cooling combustors[J].Journal of Aerospace Power,2012,27(4):832-836.(in Chinese)
[5]杨成凤,张靖周,杨卫华.全覆盖气膜孔阵列方式对冷却特性的影响[J].航空动力学报,2010,25(7):1524-1529.YANG Chengfeng,ZHANG Jingzhou,YANG Weihua.Effect of holes array arrangement on the full coverage film cooling characteristic[J].Journal of Aerospace Power,2010,25(7):1524-1529.(in Chinese)
[6]王湛,张超,刘建军.平板圆孔气膜冷却的热弹耦合分析[J].航空动力学报,2015,30(6):1298-1306.WANG Zhan,ZHANG Chao,LIU Jianjun.Thermo-elastic couplinganalysis of round-hole flat-plate film-cooling[J].Journal of Aerospace Power,2015,30(6):1298-1306.(in Chinese)
[7]GLASS D E.Ceramic matrix composite(CMC)thermal protection systems(TPS)and hot structures for hypersonic vehicles1[R].AIAA-2008-2682,2008.
[8]SOMMERS A,WANG Q,HAN X.Ceramics and ceramic matrix composites for heat exchangers in advanced thermal systems:a review[J].Applied Thermal Engineering,2010,30(11):1277-1291.
[9]KOZLOV A AVOROBIEW A GBOROVIK I N,et al.Development liquid rocket engine of small thrust with combustion chamber from carbon-ceramic composite material[M].Rijeka,Croatia:INTECH Open Access Publisher,2011.
[10]AKASHI T,TAKESHI N,KOOM T.Research of CMC application to turbine components[J].Engineering Review,2005,38(1):58.
[11]BARNARD P,HENDERSON M B,RHODES N.CMC integration and demonstration for gas turbine engines(CINDERS)[J].Applied Thermal Engineering,2004,24(11):1755-1764.
[12]张均峰,牡丹,卞祥德.复合材料主动冷却薄壁燃烧室设计分析[J].航空动力学报,2013,28(11):2401-2407.ZHANG Junfeng,MU Dan,BIAN Xiangde.Design analysis of active cooling composite combustion chamber with thin wall[J].Journal of Aerospace Power,2013,28(11):2401-2407.(in Chinese)
[13]彭丽娜,何国强,刘佩进,等.耐高温复合材料的主动冷却实验[J].宇航学报,2008,29(5):1668-1672.PENG Lina,HE Guoqiang,LIU Peijin,et al.Experiments and numerical simulation of active cooling ceramic matrix composite[J].Journal of Astronautics,2008,29(5):1668-1672.(in Chinese)
[14]WADIA A R.Advanced combustor liner cooling technology for gas turbines[J].Defence Science Journal,2014,38(4):363-380.
[15]ZHONG Fengquan,BROWN G L.A 3-dimensional,coupled,DNS,heat transfer model and solution for multi-hole cooling[J].International Journal of Heat and Mass Trannsfer,2007,50(7):1328-1343.
[16]李典森,卢子兴,刘振国,等.三维五向编织复合材料导热性能的有限元分析[J].航空动力学报,2008,23(8):1455-1460.LI Diansen,LU Zixing,LIU Zhenguo,et al.Finite element analysis of thermal conductivity of three dimensional and five directional braided composites[J].Journal of Aerospace Power,2008,23(8):1455-1460.(in Chinese)
[17]张建可.树脂基碳纤维复合材料的热物理性能之一——导热系数[J].中国空间科学技术,1987,7(3):55-60.ZHANG Jianke.The one of thermal physical properties of carbon fibre/epoxy—resin composites-thermal conductivity[J].Chinese Space Science and Technology,1987,7(3):55-60.(in Chinese)
[18]马青松,刘海韬,潘余,等.C/SiC复合材料在超燃冲压发动机中的应用研究进展[J].无机材料学报,2013,28(3):247-255.MA Qingsong,LIU Haitao,PAN Yu,et al.Research progress on the application of C/SiC composites in scramjet[J].Jouranl of Inorganic Materials,2013,28(3):247-255.(in Chinese)
[19]陈洁,熊翔,肖鹏.单向C/C复合材料导热系数的计算[J].炭素技术,2008,27(2):1-4.CHEN Jie,XIONG Xiang,XIAO Peng.Calculation of thermal conductivity coefficient in undirectional carbon/carbon composite[J].Carbon Techniques,2008,27(2):1-4.(in Chinese)