带肋横流通道中气膜孔位置对气膜冷却特性的影响

李春林; 朱惠人; 白江涛; 杜小琴; 周雷声

带肋横流通道中气膜孔位置对气膜冷却特性的影响

西北工业大学动力与能源学院,西安 710072

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出版历程
- 收稿日期: 2011-06-20
- 刊出日期: 2012-06-28

Effect of film cooling hole entrance position on film cooling characters in the cross-flow passage with ribs

School of Power and Energy, Northwestern Polytechnical University,Xi'an 710072,China

摘要

摘要: 采用数值模拟方法研究了横流通道中气膜孔与肋的相对位置对气膜冷却传热系数和冷却效率的影响.分析了吹风比为0.5,1,2,横流比为0.39,0.585,0.78时孔靠近上游肋、下游肋以及在两肋中间时对冷却效果的影响,研究结果表明:孔位于两肋中间时,气体进入孔时受的冲击较大,外表面传热系数和冷却效率较高;孔靠近上游肋时,气体孔内流动更加均匀,外表面传热系数和冷却效率均较低.
- 气膜冷却 /
- 横流通道 /
- 肋 /
- 相对位置 /
- 数值模拟
Abstract: Effect of the relative position between film cooling holes and ribs on the film cooling effectiveness and heat transfer in a channel with cross-flow and ribs was investigated numerically.The effect of position where film cooling holes were close to upstream ribs,downstream ribs and in the middle region of ribs on the cooling effect was studied with blowing ratio of 0.5,1 and 2,with cross-flow ratio of 0.39,0.585 and 0.78.The results show that,in the case of the film cooling hole entrance in the middle of two ribs,the flow in the hole are influenced heavily by the entrance jet,the heat transfer coefficient and film cooling effectiveness are higher.In the case of the film cooling hole entrance near the up-stream rib,the heat transfer coefficient and film cooling effectiveness are lower.
- film cooling /
- cross-flow passage /
- rib /
- relative position /
- numerical simulation

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参考文献(18)

[1]	林宏镇,汪火光,蒋章焰.高性能航空发动机传热技术[M].北京:国防工业出版社,2005.
[2]	葛绍岩,徐靖中.气膜冷却[M].北京:科学出版社,1985.
[3]	Bogard D G,Thole K A.Gas turbine film cooling[J].Journal of Propulsion and Power,2006,22(2):249-270.
[4]	Hay N,Lampard D,Benmansour S.Effect of cross flows on the discharge coefficient of film cooling holes[J].ASME Journal of Engineering for Power,1983,105(4):791-798.
[5]	Burd S W,Simon T W.Measurements of discharge coefficients in film cooling[J].ASME Journal of Turbomachinery,1999,121(1):243-248.
[6]	Colban W,Gratton A,Thole K.Heat transfer and film-cooling measurements on a stator vane with fan-shaped cooling holes[J].Journal of Turbomachinary,2006,128(1):53-61.
[7]	Goldstein R J,Eckert E R.Effects of hole geometry and density on three-dimensional film cooling[J].International Journal of Heat Mass Transfer,1974,17(2):595-607.
[8]	Ekkad S V,Huang Y,Han J C.Detailed heat transfer distributions in two pass square channels with rib turbulators and bleed holes[J].International Journal of Heat and Mass Transfer,1998,41(23):3781-3791.
[9]	Gritsch M,Schulz A,Wittig S.Film cooling holes with expanded exits:near hole heat transfer coefficients[J].International Journal of Heat and Fluid Flow,2000,21(2):146-155.
[10]	邓宏武,谭艳,王佳仁,等.带交错肋结构涡轮叶片复合通道的实验[J].航空动力学报,2010,25(9):1931-1937. DENG Hongwu,TAN Yan,WANG Jiaren,et al.Experimental study on the turbine blade cooling channel with crossed ribs[J].Journal of Aerospace Power,2010,25(9):1931-1937.(in Chinese)
[11]	朱剑琴,徐国强,陶智,等.带肋变截面回转通道内流动与传热的数值模拟[J].北京航空航天大学学报,2009,35(1):18-22. ZHU Jianqin,XU Guoqiang,TAO Zhi,et al.Numerical investigation of heat transfer and flow resistance in U-shaped variable crossection channelsw ith different rib heights[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(1):18-22.(in Chinese)
[12]	姚玉,张靖周,郭文.气膜孔角度对导叶冷却效果影响的数值研究[J].航空动力学报,2009,24(3):508-512. YAO Yu,ZHANG Jingzhou,GUO Wen.Numerical investigation on film cooling effectiveness of stator blade with different angles[J].Journal of Aerospace Power,2009,24(3):508-512.(in Chinese)
[13]	白江涛,朱惠人,刘存良.内通道交错横流对气膜冷却效率的影响[J].航空动力学报,2008,23(8):1353-1359. BAI Jiangtao,ZHU Huiren,LIU Cunliang.Numerical study of the effect of internal coolant crossflow on film cooling effectiveness[J].Journal of Aerospace Power,2008,23(8):1353-1359.(in Chinese)
[14]	郭涛,朱惠人,许都纯.带90°肋和双排出流孔通道传热特性的实验[J].航空动力学报,2010,25(10):2249-2254. GUO Tao,ZHU Huiren,XU Duchun.Heat transfer investigation of the channels with 90° rib turbulators and double row bleed holes[J].Journal of Aerospace Power,2010,25(10):2249-2254.(in Chinese)
[15]	李广超,朱惠人,郭涛.带60°肋和气膜孔矩形通道传热研究[J].航空动力学报,2006,21(6):995-1001. LI Guangchao,ZHU Huiren,GUO Tao.Heat transfer in the rectangular passage with 60-degree ribs and film holes[J].Journal of Aerospace Power,2006,21(6):995-1001.
[16]	Silieti M,Divo E,Kassab A.The effect of conjugate heat transfer on film cooling effectiveness[J].Numerical Heat Transfer Part B,2010,56(5):335-350.
[17]	Silieti M,Divo E,Kassab A.Numericalinvestigation of adiabatic and conjugate film cooling effectiveness on a single cylindrical film cooling hole .ASME,IMECE 2004-62196,2004.
[18]	Kassab A J,Divo E,Heidmann J D,et al.BEM/FVM conjugate heat transfer analysis of a three-dimensional film cooled turbine blade[J].International Journal for Numerical Methods in HeaTransfer and Fluid Flow,2003,13(5):581-610.