非定常尾迹输运对动叶气膜冷却流场影响

周莉; 韦威; 蔡元虎

非定常尾迹输运对动叶气膜冷却流场影响

西北工业大学动力与能源学院,西安 710072

基金项目: 国家自然科学基金(50906071); 西北工业大学基础研究基金(JC201011); 西北工业大学翱翔之星

计量
- 文章访问数: 1465
- HTML浏览量: 2
- PDF量: 721
- 被引次数: 0
出版历程
- 收稿日期: 2011-09-07
- 刊出日期: 2012-08-28

Effect of unsteady wake transportation on film cooling flowfield of rotating turbine blade

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

摘要

摘要: 对不同尾迹宽度下涡轮动叶的气膜冷却流场进行非定常数值研究,研究了尾迹输运对动叶气膜冷却流场的影响机理.计算结果表明:非定常尾迹的总压损失和速度损失而形成低速区,当非定常尾迹输运到冷却孔附近时,尾迹对气膜层的干扰占主导地位,靠近气膜孔的叶片区域冷却效率降低明显.非定常尾迹的影响使得冷却气流被带到压力面叶片下游更广阔的区域,导致气膜冷却沿叶展方向的覆盖范围更广,从而使得压力面气膜冷却效率在尾迹通过时更高一些.当尾迹宽度增大时,对气膜冷却效率的影响程度增大.尾迹对压力面的影响比吸力面更大一些.
- 尾迹输运 /
- 尾迹宽度 /
- 冷却效率 /
- 压力面 /
- 吸力面
Abstract: Unsteady flowfield of the turbine blade with film cooling was investigated numerically under different blowing rates with the wake simulated by the cylinder rod.The effect of unsteady wake transportation on the film cooling flowfield was analyzed.Results show a zone with low velocity forms due to the total pressure defection and velocity defection.The disturbance of the unsteady dominates the formation of the cooling film when the unsteady wake is transported to the position near the cooling hole,which results in the obvious reduction of the cooling effectiveness near the cooling hole.The cooling gas can be transported to the farther downstream region due to effect of the unsteady wake,and the recovery range of the cooling gas along the spanwise direction is wider than the time without unsteady wake passing,therefore better cooling effectiveness exists on the pressure surface when the unsteady wake is transported to the position near the cooling hole on the pressure surface.The effect of the unsteady wake on the cooling effectiveness increases with the increment of the width of the unsteady wake.The effect of the unsteady wake is larger on the pressure surface than that on the suction surface.
- wake transportation /
- wake width /
- film cooling effectiveness /
- pressure surface /
- suction surface

HTML

参考文献(15)

[1]	戴萍,林枫.气膜孔形状对涡轮叶片气膜冷却效果的影响[J] .热能动力工程,2009,24(5):560-565. DAI Ping,LIN Feng.Influence of air-film hole shapes on turbine blade air-film cooling effectiveness[J].Journal of Engineering for Thermal Energy & Power,2009,24(5):560-565.(in Chinese)
[2]	杨彬,徐国强,吴宏伟.旋转状态下气膜冷却换热特性的实验研究[J].航空学报,2009,30(10):1809-1815. YANG Bin,XU Guoqiang,WU Hongwei.Heat transfer measurements on a rotating film cooling model[J].Acta Aeronautica et Astronautica Sinica,2009,30(10):1809-1815.(in Chinese)
[3]	Gao Z,Narzary D P,Han J.Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J].International Journal of Heat and Mass Transfer,2008,51(10):2139-2152.
[4]	Gomes R A,Niehuis R.Film cooling effectiveness measurements with periodic unsteady inflow on highly loaded blades with main flow separation .ASME Paper GT 2009-59791,2009.
[5]	Shantanu M,Je-Chin H.Effect of unsteady wake on full coverage film-cooling effectiveness for a gas turbine blade .AIAA Paper,AIAA 2006-3403,2006.
[6]	Kim S,Ibrahim G H.Unsteady heat transfer analysis of a film cooling flow .AIAA Paper AIAA 2008-1287,2008.
[7]	Womack K M,Volino R J,Schultz M P.Measurement in film cooling flows with periodic wake[J].Journal of Turbomachinery,2008,130(4):1008-1017.
[8]	Shantanu M,Je-Chin H.Effect of unsteady wake on full coverage film-cooling effectiveness for a gas turbine blade .AIAA Paper AIAA 2006-3403,2006.
[9]	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.
[10]	蒋雪辉,赵晓路.非定常尾迹对叶片头部气膜冷却的影响[J].航空动力学报,2005,20(4):540-544. JUANG Xuehui,ZHAO Xiaolu.The effect of unsteady wake on leading edge film cooling[J].Journal of Aerospace Power,2005,20(4):540-544.(in Chinese)
[11]	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)
[12]	周勇,赵晓路,徐建中.非定常激波对气膜冷却影响的数值模拟[J].工程热物理学报,2007,28(6):933-935. ZHOU Yong,ZHAO Xiaolu,XU Jianzhong.Numeical simulation of the unsteady effect of upstream shock on flim-cooling in a 1+1/2 turbine stage[J].Journal of Engineering Thermophysics,2007,28(6):933-935.(in Chinese)
[13]	李少华,李知骏,曲宏伟.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):3-6. LI Shaohua,LI Zhijun,QU Hongwei.Numerical simulation study on the effect of unsteady wakes on leading edge film cooling[J].Power System Engineering,2011,27(1):3-6.(in Chinese)
[14]	Volker S,Howard P H.Unsteady wake-induced boundary layer transition in high lift LP turbines .ASME Paper GT 96-486,1996.
[15]	Schulte V,Hodson H P.Wake-separation bubble interaction in low pressure turbines .AIAA Paper AIAA-94-2931,1994.