尾迹对涡轮动叶全表面气膜冷却效率的影响
|
摘要
采用压敏漆(PSP)测量技术研究了尾迹对涡轮动叶气膜冷却效率的影响,测试叶片带有11排圆柱形气膜孔。获得了不同质量流量比和尾迹斯特劳哈尔数(Sr=0,0.12,0.36)条件下全表面气膜冷却效率分布的试验数据,结果表明:随着尾迹Sr数的增加,叶片前缘区域径向平均气膜冷却效率最大降低幅度达36.5%,吸力面径向平均气膜冷却效率最大降低幅度达53.5%,压力面径向平均气膜冷却效率最大降低幅度达24.2%;尾迹对前缘和吸力面气膜冷却效率的影响大于压力面;随着质量流量比增加,尾迹的影响减小;在进行涡轮动叶表面气膜冷却结构设计时,不考虑尾迹效应会增加设计风险。
The effect of unsteady wake on the film cooling effectiveness of the turbine blade is studied using the Pressure Sensitive Paint(PSP)measurement technique.The test blade has eleven rows of cylindrical film holes.The distribution of the film cooling effectiveness on the whole blade surface under different mass flux ratios and different wake Strouhal numbers(Sr=0,0.12,0.36)are obtained.The results show that as the wake Strouhal number increases,the radial averaged film cooling effectiveness of the leading edge decreases by up to 36.5%,the radial averaged film cooling effectiveness of the suction surface decreases by up to 53.5%,and that of the pressure surface decreases by up to 24.2%.The effect of wake on the leading edge and the suction surface is greater than that on the pressure surface.As the mass flux ratio increases,the effect of the unsteady wake decreases.When designing the cooling structure of the turbine blade,ignoring the effect of the wake increases the design risk.
The effect of unsteady wake on the film cooling effectiveness of the turbine blade is studied using the Pressure Sensitive Paint(PSP)measurement technique.The test blade has eleven rows of cylindrical film holes.The distribution of the film cooling effectiveness on the whole blade surface under different mass flux ratios and different wake Strouhal numbers(Sr=0,0.12,0.36)are obtained.The results show that as the wake Strouhal number increases,the radial averaged film cooling effectiveness of the leading edge decreases by up to 36.5%,the radial averaged film cooling effectiveness of the suction surface decreases by up to 53.5%,and that of the pressure surface decreases by up to 24.2%.The effect of wake on the leading edge and the suction surface is greater than that on the pressure surface.As the mass flux ratio increases,the effect of the unsteady wake decreases.When designing the cooling structure of the turbine blade,ignoring the effect of the wake increases the design risk.
引文
[1]FERNANDES C P,VOET M T,LITTLE Z,et al.Flow statistics and visualisation of multi-row film cooling boundary layers:GT2017-64391[R].New York:ASME,2017.
[2]朱惠人,许都纯,刘松龄,等.簸箕形排孔气膜冷却实验研究[J].航空学报,1997,18(5):25-28.ZHU H R,XU D C,LIU S L,et al.Film cooling experimental investigation of a row of dust-pan shaped holes[J].Acta Aeronautica et Astronautica Sinica,1997,18(5):25-28(in Chinese).
[3]韩振兴,末永洁,刘石.吹风比对气膜冷却效率影响的实验研究[J].航空学报,2004,25(6):551-555.HAN Z X,MO Y J,LIU S.Experimental research on film cooling effectivenesses at different blowing ratios[J].Acta Aeronautica et Astronautica Sinica,2004,25(6):551-555(in Chinese).
[4]李广超,张魏,彭大维,等.带锥形扩张支孔射流气膜冷却效率数值模拟[J].航空学报,2010,31(7):1360-1365.LI G C,ZHANG W,PENG D W,et al.Numerical simulation of film cooling effectiveness with conical expanded branch holes[J].Acta Aeronautica et Astronautica Sinica,2010,31(7):1360-1365(in Chinese).
[5]游良平,陶毓伽,蔡军,等.涡轮叶片前缘复合冷却实验[J].航空学报,2009,30(9):1618-1623.YOU L P,TAO Y J,CAI J,et al.Experiment of composite cooling on leading edge of turbine blade[J].Acta Aeronautica et Astronautica Sinica,2009,30(9):1618-1623(in Chinese).
[6]WIESE C J,RUTLEDGE J L,POLANKA M D.Experimental evaluation of thermal and mass transfer techniques to measure adiabatic effectiveness with various coolant to freestream property ratios:GT2017-65019[R].New York:ASME,2017.
[7]MCCLINTIC J W,ANDERSON J B,BOGARD D G,et al.Effect of internal crossflow velocity on film cooling effectiveness-Part I:Axial shaped holes:GT2017-64616[R].New York:ASME,2017.
[8]MCCLINTIC J W,ANDERSON J B,BOGARD D G,et al.Effect of internal crossflow velocity on film cooling effectiveness-Part II:Compound angle shaped holes:GT2017-64624[R].New York:ASME,2017.
[9]姚玉,张靖周,何飞,等.涡轮叶片吸力面上收敛缝形孔气膜冷却效率的数值研究[J].航空学报,2010,31(6):1115-1120.YAO Y,ZHANG J Z,HE F,et al.Numerical investigation on film cooling effectiveness of converging slot hole at turbine blade suction surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(6):1115-1120(in Chinese).
[10]丁阳,常海萍,杜治能.多排反向射流角气膜冷却特性研究[J].航空学报,2013,34(11):2472-2481.DING Y,CHANG H P,DU Z N.Investigation on characteristics of multiple rows of opposite lateral ejection angle film cooling[J].Acta Aeronautica et Astronautica Sinica,2013,34(11):2472-2481(in Chinese).
[11]刘存良,朱惠人,白江涛,等.涡轮叶片上收缩-扩张形孔排的全表面气膜冷却特性[J].航空学报,2010,31(4):687-693.LIU C L,ZHU H R,BAI J T,et al.Experimental research on film cooling characteristics of converging-expanding hole rows on turbine blade surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(4):687-693(in Chinese).
[12]SEO H J,LEE J S,LIGRANI P M.Effects of bulk flow pulsations on film cooling from different length injection holes at different blowing ratios:98-GT-192[R].New York:ASME,1998.
[13]JUNG I S,LEE J S.Effects of bulk flow pulsations on film cooling from spanwise oriented holes:98-GT-211[R]:New York:ASME,1998.
[14]LEE J S,JUNG I S.Effect of bulk flow pulsations on film cooling with compound angle holes[J].International Journal of Heat&Mass Transfer,2002,45(1):113-123.
[15]NIKPARTO A,RICE T,SCHOBEIRI M T.Experimental and numerical investigation of heat transfer and film cooling effectiveness of a highly loaded turbine blade under steady and unsteady wake flow condition:GT2017-65012[R].New York:ASME,2017.
[16]LU X G,ZHANG Y F,LI W,et al.Effects of periodic wakes on boundary layer development on an ultra-high-lift low pressure turbine airfoil[J].Proceedings of the Institution of Mechanical Engineers Part A-Journal of Power&Energy,2016,231(1):25-38.
[17]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 X H,ZHAO X L.Effect of unsteady wake on linear cascade film cooling efficiency[J].Journal of Propulsion Technology,2004,25(4):311-315(in Chinese).
[18]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 X H,ZHAO X L.Numerical simulation of the unsteady wakes effects on film cooling[J].Journal of Engineering Thermophysics,2005,26(2):322-324(in Chinese).
[19]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.JIANG X H,ZHAO X L.The effect of unsteady wake on leading edge film cooling[J].Journal of Aerospace Power,2005,20(4):540-544(in Chinese).
[20]GUENETTE G R,EPSTEIN A H,GILES M B,et al.Fully scaled transonic turbine rotor heat transfer measurements[J].Journal of Turbomachinery,1989,111(1):1-7.
[21]BRIEN 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]朱惠人,许都纯,刘松龄,等.簸箕形排孔气膜冷却实验研究[J].航空学报,1997,18(5):25-28.ZHU H R,XU D C,LIU S L,et al.Film cooling experimental investigation of a row of dust-pan shaped holes[J].Acta Aeronautica et Astronautica Sinica,1997,18(5):25-28(in Chinese).
[3]韩振兴,末永洁,刘石.吹风比对气膜冷却效率影响的实验研究[J].航空学报,2004,25(6):551-555.HAN Z X,MO Y J,LIU S.Experimental research on film cooling effectivenesses at different blowing ratios[J].Acta Aeronautica et Astronautica Sinica,2004,25(6):551-555(in Chinese).
[4]李广超,张魏,彭大维,等.带锥形扩张支孔射流气膜冷却效率数值模拟[J].航空学报,2010,31(7):1360-1365.LI G C,ZHANG W,PENG D W,et al.Numerical simulation of film cooling effectiveness with conical expanded branch holes[J].Acta Aeronautica et Astronautica Sinica,2010,31(7):1360-1365(in Chinese).
[5]游良平,陶毓伽,蔡军,等.涡轮叶片前缘复合冷却实验[J].航空学报,2009,30(9):1618-1623.YOU L P,TAO Y J,CAI J,et al.Experiment of composite cooling on leading edge of turbine blade[J].Acta Aeronautica et Astronautica Sinica,2009,30(9):1618-1623(in Chinese).
[6]WIESE C J,RUTLEDGE J L,POLANKA M D.Experimental evaluation of thermal and mass transfer techniques to measure adiabatic effectiveness with various coolant to freestream property ratios:GT2017-65019[R].New York:ASME,2017.
[7]MCCLINTIC J W,ANDERSON J B,BOGARD D G,et al.Effect of internal crossflow velocity on film cooling effectiveness-Part I:Axial shaped holes:GT2017-64616[R].New York:ASME,2017.
[8]MCCLINTIC J W,ANDERSON J B,BOGARD D G,et al.Effect of internal crossflow velocity on film cooling effectiveness-Part II:Compound angle shaped holes:GT2017-64624[R].New York:ASME,2017.
[9]姚玉,张靖周,何飞,等.涡轮叶片吸力面上收敛缝形孔气膜冷却效率的数值研究[J].航空学报,2010,31(6):1115-1120.YAO Y,ZHANG J Z,HE F,et al.Numerical investigation on film cooling effectiveness of converging slot hole at turbine blade suction surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(6):1115-1120(in Chinese).
[10]丁阳,常海萍,杜治能.多排反向射流角气膜冷却特性研究[J].航空学报,2013,34(11):2472-2481.DING Y,CHANG H P,DU Z N.Investigation on characteristics of multiple rows of opposite lateral ejection angle film cooling[J].Acta Aeronautica et Astronautica Sinica,2013,34(11):2472-2481(in Chinese).
[11]刘存良,朱惠人,白江涛,等.涡轮叶片上收缩-扩张形孔排的全表面气膜冷却特性[J].航空学报,2010,31(4):687-693.LIU C L,ZHU H R,BAI J T,et al.Experimental research on film cooling characteristics of converging-expanding hole rows on turbine blade surface[J].Acta Aeronautica et Astronautica Sinica,2010,31(4):687-693(in Chinese).
[12]SEO H J,LEE J S,LIGRANI P M.Effects of bulk flow pulsations on film cooling from different length injection holes at different blowing ratios:98-GT-192[R].New York:ASME,1998.
[13]JUNG I S,LEE J S.Effects of bulk flow pulsations on film cooling from spanwise oriented holes:98-GT-211[R]:New York:ASME,1998.
[14]LEE J S,JUNG I S.Effect of bulk flow pulsations on film cooling with compound angle holes[J].International Journal of Heat&Mass Transfer,2002,45(1):113-123.
[15]NIKPARTO A,RICE T,SCHOBEIRI M T.Experimental and numerical investigation of heat transfer and film cooling effectiveness of a highly loaded turbine blade under steady and unsteady wake flow condition:GT2017-65012[R].New York:ASME,2017.
[16]LU X G,ZHANG Y F,LI W,et al.Effects of periodic wakes on boundary layer development on an ultra-high-lift low pressure turbine airfoil[J].Proceedings of the Institution of Mechanical Engineers Part A-Journal of Power&Energy,2016,231(1):25-38.
[17]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 X H,ZHAO X L.Effect of unsteady wake on linear cascade film cooling efficiency[J].Journal of Propulsion Technology,2004,25(4):311-315(in Chinese).
[18]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 X H,ZHAO X L.Numerical simulation of the unsteady wakes effects on film cooling[J].Journal of Engineering Thermophysics,2005,26(2):322-324(in Chinese).
[19]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.JIANG X H,ZHAO X L.The effect of unsteady wake on leading edge film cooling[J].Journal of Aerospace Power,2005,20(4):540-544(in Chinese).
[20]GUENETTE G R,EPSTEIN A H,GILES M B,et al.Fully scaled transonic turbine rotor heat transfer measurements[J].Journal of Turbomachinery,1989,111(1):1-7.
[21]BRIEN 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.