尾迹对动叶表面簸箕孔气膜冷却影响实验
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摘要
采用压敏漆(PSP)技术研究了上游尾迹对吸力面和压力面带有单排簸箕形气膜孔的涡轮动叶表面气膜冷却效率的影响,获得了不同吹风比(0.25～1.5)和尾迹斯特劳哈尔数(0、0.12、0.36)条件下涡轮叶片表面气膜冷却效率分布的实验数据,结果表明:尾迹使吸力面簸箕孔后径向平均气膜冷却效率最大下降幅度达0.07,使压力面簸箕孔后径向平均气膜冷却效率最大下降幅度达0.024;有尾迹时,随着吹风比的增加,吸力面气膜孔后冷却效率逐渐降低,压力面气膜孔后冷却效率先增加后降低。
The effect of unsteady wake on the film cooling effectiveness of the turbine blade was studied using the pressure sensitive paint(PSP)measurement technique.The test blade had two rows of dust-pan shaped film holes on the suction surface and the pressure surface,respectively.The blowing ratio varied from 0.25 to 1.5 and the wake Strouhal number of 0,0.12,0.36.Results showed that as the wake Strouhal number increased,the spanwise averaged film cooling effectiveness of the suction surface decreased by up to 0.07 and the span-wise averaged film cooling effectiveness of the pressure surface decreased by up to0.024.For the wake cases,an increase in the blowing ratio caused a decrease in film cooling effectiveness on the suction surface.The film cooling effectiveness increased first and then decreased on the pressure surface as the blowing ratio increased.
The effect of unsteady wake on the film cooling effectiveness of the turbine blade was studied using the pressure sensitive paint(PSP)measurement technique.The test blade had two rows of dust-pan shaped film holes on the suction surface and the pressure surface,respectively.The blowing ratio varied from 0.25 to 1.5 and the wake Strouhal number of 0,0.12,0.36.Results showed that as the wake Strouhal number increased,the spanwise averaged film cooling effectiveness of the suction surface decreased by up to 0.07 and the span-wise averaged film cooling effectiveness of the pressure surface decreased by up to0.024.For the wake cases,an increase in the blowing ratio caused a decrease in film cooling effectiveness on the suction surface.The film cooling effectiveness increased first and then decreased on the pressure surface as the blowing ratio increased.
引文
[1]HAYDT S,LYNCH S,LEWIS S.The effect of area ratio change via increased hole length for shaped film cooling holes with constant expansion angles[R].ASME Paper GT2017-63692,2017.
[2]FUNAZAKI K I.Enhancement of film effectiveness of cooling holes with fan-shaped exit geometry by the application of double flow-control devices:optimization in consideration of device offset[R].ASME Paper GT2017-65032,2017.
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[4]李永康,张靖周,姚玉.利用三角形突片改善气膜冷却效率的数值研究[J].航空动力学报,2006,21(1):83-87.LI Yongkang,ZHANG Jingzhou,YAO Yu.Numerical investigation on improvement of film cooling effectiveness using delta-shaped tabs[J].Journal of Aerospace Power,2006,21(1):83-87.(in Chinese)
[5]范宜龙,朱惠人,李永红,等.逆压力梯度下几何参数对气膜冷却效率的影响[J].航空动力学报,2010,25(8):1738-1745.FAN Yilong,ZHU Huiren,LI Yonghong,et al.Influence of geometric parameters on film cooling effectiveness under adverse pressure gradient[J].Journal of Aerospace Power,2010,25(8):1738-1745.(in Chinese)
[6]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):507-512.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):507-512.(in Chinese)
[7]ANDERSON J B,MCCLINTIC J W,BOGARD D G,et al.Freestream flow effects on film effectiveness and heat transfer coefficient augmentation for compound angle shaped holes[R].ASME Paper GT2017-64853,2017.
[8]SHIAU C C,CHOWDHURY N H K,HAN J C,et al.Transonic turbine vane suction side film cooling with showerhead effect using psp measurement technique[R].ASME Paper GT2017-63143,2017.
[9]JIN Y J,KWAK J S,PARK J S,et al.Measurement of film cooling effectiveness for the first-stage vane and endwall of agas turbine with fan-shaped holes[R].ASME Paper GT2017-63896,2017.
[10]向安定,罗小强,朱惠人,等.涡轮叶片表面气膜冷却的传热实验研究[J].航空动力学报,2002,17(5):577-581.XIANG Anding,LUO Xiaoqiang,ZHU Huiren,et al.Turbine blade surface heat transfer and film cooling measurements in a turbine cascade with injection on surface[J].Journal of Aerospace Power,2002,17(5):577-581.(in Chinese)
[11]STRATTON Z T,SHIH T,LASKOWSKI G M,et al.Effects of crossflow in an internal cooling channel on film cooling of a flat plate through compound angle hole[R].ASME Paper GT2015-42771,2015.
[12]DU H,HAN J C,EKKAD S V.Effect of unsteady wake on detailed heat transfer coefficient and film effectiveness distributions for a gas turbine blade[R].ASME Paper 97-GT-166,1997.
[13]LI S J,RALLABANDI A P,HAN J C.Influence of unsteady wake with trailing edge coolant ejection on turbine blade film cooling[R].ASME Paper GT2011-45925,2011.
[14]LI S J,YANG S F,HAN J C,et al.Turbine blade surface phantom cooling from upstream nozzle trailing-edge ejection[J].Journal of Thermophysics and Heat Transfer,2015,5:1-12.
[15]RALLABANDI A P.Unsteady wake and coolant density effects on turbine blade film cooling using pressure sensitive paint technique[J].Journal of Heat Transfer,2012,134(8):1-10.
[16]GOMES R A,NIEHUIS R.Film cooling effectiveness measurements with periodic unsteady inflow on highly loaded blades with main flow separation[R].ASME Paper GT2009-59791,2009.
[17]印洲.上游尾迹对气膜冷却影响的研究[D].南京:南京航空航天大学,2016.YIN Zhou.Investigation for effect of upstream wake on film cooling characteristics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2016.(in Chinese)
[18]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,2011,26(5):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,2011,26(5):818-821.(in Chinese)
[19]OBRIEN J E,CAPP S P.Two-component phase-averaged turbulence statistics downstream of a rotating spokedwheel wake generator[J].Journal of Turbomachinery,1989,111(4):475-482.
[2]FUNAZAKI K I.Enhancement of film effectiveness of cooling holes with fan-shaped exit geometry by the application of double flow-control devices:optimization in consideration of device offset[R].ASME Paper GT2017-65032,2017.
[3]章大海,陈秋炀,曾敏,等.不同横槽结构对气膜冷却效率影响的数值研究[J].航空动力学报,2008,23(4):611-616.ZHANG Dahai,CHEN Qiuyang,ZENG Min,et al.Numerical investigation on the effect of different transverse trench configurations on film cooling effectiveness[J].Journal of Aerospace Power,2008,23(4):611-616.(in Chinese)
[4]李永康,张靖周,姚玉.利用三角形突片改善气膜冷却效率的数值研究[J].航空动力学报,2006,21(1):83-87.LI Yongkang,ZHANG Jingzhou,YAO Yu.Numerical investigation on improvement of film cooling effectiveness using delta-shaped tabs[J].Journal of Aerospace Power,2006,21(1):83-87.(in Chinese)
[5]范宜龙,朱惠人,李永红,等.逆压力梯度下几何参数对气膜冷却效率的影响[J].航空动力学报,2010,25(8):1738-1745.FAN Yilong,ZHU Huiren,LI Yonghong,et al.Influence of geometric parameters on film cooling effectiveness under adverse pressure gradient[J].Journal of Aerospace Power,2010,25(8):1738-1745.(in Chinese)
[6]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):507-512.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):507-512.(in Chinese)
[7]ANDERSON J B,MCCLINTIC J W,BOGARD D G,et al.Freestream flow effects on film effectiveness and heat transfer coefficient augmentation for compound angle shaped holes[R].ASME Paper GT2017-64853,2017.
[8]SHIAU C C,CHOWDHURY N H K,HAN J C,et al.Transonic turbine vane suction side film cooling with showerhead effect using psp measurement technique[R].ASME Paper GT2017-63143,2017.
[9]JIN Y J,KWAK J S,PARK J S,et al.Measurement of film cooling effectiveness for the first-stage vane and endwall of agas turbine with fan-shaped holes[R].ASME Paper GT2017-63896,2017.
[10]向安定,罗小强,朱惠人,等.涡轮叶片表面气膜冷却的传热实验研究[J].航空动力学报,2002,17(5):577-581.XIANG Anding,LUO Xiaoqiang,ZHU Huiren,et al.Turbine blade surface heat transfer and film cooling measurements in a turbine cascade with injection on surface[J].Journal of Aerospace Power,2002,17(5):577-581.(in Chinese)
[11]STRATTON Z T,SHIH T,LASKOWSKI G M,et al.Effects of crossflow in an internal cooling channel on film cooling of a flat plate through compound angle hole[R].ASME Paper GT2015-42771,2015.
[12]DU H,HAN J C,EKKAD S V.Effect of unsteady wake on detailed heat transfer coefficient and film effectiveness distributions for a gas turbine blade[R].ASME Paper 97-GT-166,1997.
[13]LI S J,RALLABANDI A P,HAN J C.Influence of unsteady wake with trailing edge coolant ejection on turbine blade film cooling[R].ASME Paper GT2011-45925,2011.
[14]LI S J,YANG S F,HAN J C,et al.Turbine blade surface phantom cooling from upstream nozzle trailing-edge ejection[J].Journal of Thermophysics and Heat Transfer,2015,5:1-12.
[15]RALLABANDI A P.Unsteady wake and coolant density effects on turbine blade film cooling using pressure sensitive paint technique[J].Journal of Heat Transfer,2012,134(8):1-10.
[16]GOMES R A,NIEHUIS R.Film cooling effectiveness measurements with periodic unsteady inflow on highly loaded blades with main flow separation[R].ASME Paper GT2009-59791,2009.
[17]印洲.上游尾迹对气膜冷却影响的研究[D].南京:南京航空航天大学,2016.YIN Zhou.Investigation for effect of upstream wake on film cooling characteristics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2016.(in Chinese)
[18]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,2011,26(5):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,2011,26(5):818-821.(in Chinese)
[19]OBRIEN J E,CAPP S P.Two-component phase-averaged turbulence statistics downstream of a rotating spokedwheel wake generator[J].Journal of Turbomachinery,1989,111(4):475-482.