非定常尾迹宽度对动叶传热影响的数值研究
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摘要
应用Standard k-=紊流模型并结合SIMPLE算法,近壁区流动的处理采用壁面函数法,对燃气轮机首级静叶产生的非定常尾迹及动叶流场进行数值模拟。通过在动叶前放置直径为d=2、4、6 mm的圆柱来模拟静叶尾迹的宽度,研究不同时刻尾迹宽度对下游动叶传热特性的影响。结果表明:静叶产生的尾迹对下游动叶压力面与吸力面的速度影响呈现周期性变化,圆柱尾迹产生的速度亏损,使主流的流速降低,压力面低速回流区在1/4T时刻达到最大。低吹风比M=0.5时,尾迹宽度增大(d=4 mm)能使压力面传热增强,而吸力面的传热变化很小,但过高的尾迹宽度(d=6 mm)将会同时降低压力面和吸力面的努赛尔数。高吹风比M=1.5时,随着尾迹宽度增大,压力面和吸力面的传热均增强,在d=6 mm时努赛尔数达到最大。
Using the standard k- = turbulence model,SIMPLE algorithm and the wall function treatment, numerical simulation was performed to investigate in unsteady wake caused by turbine first static blade and rotor blade flow field.To change the width of wake by altering column diameter d = 2,4, 6 mm placed in front of rotor blade to study the influence of wake on the heat transfer characteristic of rotor blade at different moment. The results show that the unsteady wake caused by static blade affects the velocity of pressure side and suction side of rotor blade periodically. Velocity loss leads main stream velocity to decrease; low velocity recirculation zone comes to maximum at 1/4T. When blowing ratio M = 0.5,wake width increases to d = 4 mm will enhance heat transfer of pressure side, suction side changes slightly, while overlarge wake width d = 6 mm will decrease the Nusselt number of pressure and suction side. When blowing ratio M = 1.5, the Nusselt number of pressure and suction side will both increase with wake width increasing and comes to the maximum at d = 6 mm.
Using the standard k- = turbulence model,SIMPLE algorithm and the wall function treatment, numerical simulation was performed to investigate in unsteady wake caused by turbine first static blade and rotor blade flow field.To change the width of wake by altering column diameter d = 2,4, 6 mm placed in front of rotor blade to study the influence of wake on the heat transfer characteristic of rotor blade at different moment. The results show that the unsteady wake caused by static blade affects the velocity of pressure side and suction side of rotor blade periodically. Velocity loss leads main stream velocity to decrease; low velocity recirculation zone comes to maximum at 1/4T. When blowing ratio M = 0.5,wake width increases to d = 4 mm will enhance heat transfer of pressure side, suction side changes slightly, while overlarge wake width d = 6 mm will decrease the Nusselt number of pressure and suction side. When blowing ratio M = 1.5, the Nusselt number of pressure and suction side will both increase with wake width increasing and comes to the maximum at d = 6 mm.
引文
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[16]李少华,王成荫,吴殿文,等.非定常尾迹对叶栅温度影响的数值研究[J].东北电力大学学报,2010,30(2):1-5.Li Shaohua,Wang Chengyin,Wu Dianwen,et al.Numerical prediction of the temperature of first grade cascade on the effects of unsteady wakes[J].Journal of Northeast Dianli University,2010,30(2):1-5(in Chinese).
[17]周莉,张鑫,蔡元虎.非定常尾迹宽度对动叶气膜冷却效果的影响[J].中国电机工程学报,2011,31(29):97-102.Zhou Li,Zhang Xin,Cai Yuanhu.Effect of unsteady wake width on the film-cooling effectiveness for a gas turbine blade[J].Proceeding of the CSEE,2011,31(29):97-102(in Chinese).
[18]周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜流场影响[J].航空动力学报,2012,27(8):1696-1703.Zhou Li,Wei Wei,Cai Yuanhu.Effect of unsteady transportation on film cooling flowfield of rotating turbine blade[J].Journal of Aerospace Power,2012,27(8):1696-1703(in Chinese).
[19]周莉,张鑫,蔡元虎.非定常环境下动叶气膜冷却流场的数值模拟[J].航空动力学报,2011,26(8):1695-1701.Zhou Li,Zhang Xin,Cai Yuanhu.Unsteady numerical simulation of the turbine blade film cooling[J].Journal of Aerospace Power,2011,26(8):1695-1701(in Chinese).
[20]Yamamoto.Production and development of secondary flows and losses in two types of straight turbine cascades:part 2-A rotor case[J].Journal of Turbomachinery,1987,109(4):194-200.
[21]Schulte V,Hodson H P.Wake-separation bubble interaction in Low Pressure Turbines[C]//30th Aerospace Sciences Meeting and Exhibit,Indianapolis,Indiana,USA,1994.
[22]Volker S,Howard P H.Unsteady wake-induced boundary layer transition in high lift LP turbines[C]//Proceeding of the 1996 International Gas Turbine and Aeroengine Congress&Exhibition,Burminghan,UK,1996.
[23]杨汇涛,曹玉璋.旋转叶片端部气膜冷却的数值计算[J].航空动力学报,1998,13(3):285-289.Yang Huitao,Cao Yuzhang.Endwall film-cooling of rotated blade[J].Journal of Aerospace Power,1998,13(3):285-289(in Chinese).
[24]韩介勤,桑地普·杜达,斯瑞纳斯·艾卡德.燃气轮机传热和冷却技术[M].西安:西安交通大学出版社,2005,20-134.Je-Chin Han,Sandip Dutta,Srinath V Ekkad.Gas turbine heat transfer and cooling technology[M].Xi’an:Xi’an Jiaotong University Press,2005,20-134(in Chinese).
[2]Han J C.Influence of unsteady wake on heat transfer coefficients from a gas turbine blade[J].ASME Tournal of Heat Transfer,1993,115(4):904-911.
[3]Womack K M,Volino R J,Schultz M P.Measurment in film cooling flows with periodic wake[J].Journal of Turbomachinery,2008,130(4):1008-1017.
[4]Ekkad S V,Mehendale A B,Han J C.Combined effect of grid turbulence and unsteady wake on film effectiveness and heat transfer coefficient of a gas turbine blade with air and CO2 film injection[J].Journal of Turbomachinery,1997,119(7):594-600.
[5]Ou S,Han J-C,Mehendale A B.Unsteady wake over a linear turbine blade cascade with air and CO2 film injection:partⅠ-effect on heat transfer coefficients[J].Journal of Turbomachinery,1994,116(10):721-729.
[6]Shuye Teng,Dong Kee Sohn,Je-Chin Han.Unsteady wake effect on film temperature and effectiveness distributions for a gas turbine blade[J].Journal of Turbomachinery,2000,122(10):340-347.
[7]Arhari R S,Epstein A H.An experiment of film cooling in a rotating transonic turbine[J].Journal of Turbomachinery,1994,116(10):63~70.
[8]Montomoli F,Massini M,Adami P.Effect of incidence angle with wake passing on a film cooled leading edge:a numerical study[J].International Journal for Numerical Methods in Fluids,2010,63(12):1359-1374.
[9]蒋雪辉,赵晓路.非定常尾迹对叶栅气膜冷却效率的影响[J].推进技术,2004,25(4):311-315.Jiang Xuehui,Zhao Xiaolu.Effect of unsteady wake on linear cascade film cooling efficiency[J].Journal of Propulsion Technology,2004,25(4):311-315(in Chinese).
[10]蒋雪辉,赵晓路.非定常尾迹对气膜冷却影响的数值研究[J].工程热物理学报,2005,26(2):322-324.Jiang Xuehui,Zhao Xiaolu.Numerical simulation of the unsteady wakes effects on film cooling[J].Journal of Engineering Thermophysics,2005,26(2):322-324(in Chinese).
[11]袁锋,竺晓程,杜朝辉.尾迹对气膜冷却影响的三维非定常数值模拟[J].动力工程,2006,26(6):818-821.Yuan Feng,Zhu Xiaocheng,Du Zhaohui.Three dimensional unsteady numerical simulation of the effect of wakes on film cooling[J].Journal of Power Engineering,2006,26(6):818-821(in Chinese).
[12]袁锋,张才稳,黄海舟,等.尾迹对涡轮动叶气膜冷却三维非定常数值模拟[J].热能动力工程,2011,26(5):507-512.Yuan Feng,Zhang Caiwen,Huang Haizhou,et al.Three dimensional unsteady numerical simulation of the effect of wakes on rotor blade film cooling[J].Journal of Engineering for Thermal Energy and Power,2011,26(5):507-512(in Chinese).
[13]郭婷婷,张玲,邹晓辉,等.旋转叶片气膜冷却效果的数值研究[J].中国电机工程学报,2008,28(29):83-87.Guo Tingting,Zhang Ling,Zou Xiaohui,et al.Numerical study on the film cooling effect of rotating blades[J].Proceedings of the CSEE,2008,28(29):83-87(in Chinese).
[14]李少华,吕敏,张玲,等.非定常尾迹及其对动叶气膜冷却影响的数值研究[J].动力工程学报,2011,31(12):922-927.Li Shaohua,LüMin,Zhang Ling,et al.Numerical simulation of unsteady wakes and the influence on film-cooling effectiveness[J].Journal of Chinese Society of Power Engineering,2011,31(12):922-927(in Chinese).
[15]李少华,李知骏,曲宏伟,等.非定常尾迹对动叶气膜冷却影响的数值模拟[J].电站系统工程,2011,27(1):3-5.Li Shaohua,Li Zhijun,Qu Hongwei,et al.Numerical simulation study on the effect of unsteady wakes on leading edge film cooling[J].Power System Engineering,2011,27(1):3-5(in Chinese).
[16]李少华,王成荫,吴殿文,等.非定常尾迹对叶栅温度影响的数值研究[J].东北电力大学学报,2010,30(2):1-5.Li Shaohua,Wang Chengyin,Wu Dianwen,et al.Numerical prediction of the temperature of first grade cascade on the effects of unsteady wakes[J].Journal of Northeast Dianli University,2010,30(2):1-5(in Chinese).
[17]周莉,张鑫,蔡元虎.非定常尾迹宽度对动叶气膜冷却效果的影响[J].中国电机工程学报,2011,31(29):97-102.Zhou Li,Zhang Xin,Cai Yuanhu.Effect of unsteady wake width on the film-cooling effectiveness for a gas turbine blade[J].Proceeding of the CSEE,2011,31(29):97-102(in Chinese).
[18]周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜流场影响[J].航空动力学报,2012,27(8):1696-1703.Zhou Li,Wei Wei,Cai Yuanhu.Effect of unsteady transportation on film cooling flowfield of rotating turbine blade[J].Journal of Aerospace Power,2012,27(8):1696-1703(in Chinese).
[19]周莉,张鑫,蔡元虎.非定常环境下动叶气膜冷却流场的数值模拟[J].航空动力学报,2011,26(8):1695-1701.Zhou Li,Zhang Xin,Cai Yuanhu.Unsteady numerical simulation of the turbine blade film cooling[J].Journal of Aerospace Power,2011,26(8):1695-1701(in Chinese).
[20]Yamamoto.Production and development of secondary flows and losses in two types of straight turbine cascades:part 2-A rotor case[J].Journal of Turbomachinery,1987,109(4):194-200.
[21]Schulte V,Hodson H P.Wake-separation bubble interaction in Low Pressure Turbines[C]//30th Aerospace Sciences Meeting and Exhibit,Indianapolis,Indiana,USA,1994.
[22]Volker S,Howard P H.Unsteady wake-induced boundary layer transition in high lift LP turbines[C]//Proceeding of the 1996 International Gas Turbine and Aeroengine Congress&Exhibition,Burminghan,UK,1996.
[23]杨汇涛,曹玉璋.旋转叶片端部气膜冷却的数值计算[J].航空动力学报,1998,13(3):285-289.Yang Huitao,Cao Yuzhang.Endwall film-cooling of rotated blade[J].Journal of Aerospace Power,1998,13(3):285-289(in Chinese).
[24]韩介勤,桑地普·杜达,斯瑞纳斯·艾卡德.燃气轮机传热和冷却技术[M].西安:西安交通大学出版社,2005,20-134.Je-Chin Han,Sandip Dutta,Srinath V Ekkad.Gas turbine heat transfer and cooling technology[M].Xi’an:Xi’an Jiaotong University Press,2005,20-134(in Chinese).