单排圆柱孔射流气膜加热与气膜冷却方式的对比
|
摘要
为了揭示气膜加热和气膜冷却两种方式在影响规律机制上的异同,通过数值计算研究了两种方式单排圆柱孔在典型吹风比下(0.5,1.0和1.5)的射流-主流相干特征,并分析了热气流-冷气流温度比变化对气膜绝热加热或冷却效率的影响。研究结果表明:在相同的吹风比下,在气膜加热方式下喷注射流向主流的穿透趋向更为显著,引起喷注射流抬离壁面并在气膜孔出口附近诱导出尺度更大的卵形涡对;当温度比接近于1时,气膜绝热加热效率与气膜绝热冷却效率差异较小,随着温度比偏离1的程度加剧,气膜绝热加热效率与气膜绝热冷却效率差异显著增大。
To reveal the similarities and differences between film cooling and film heating in the physical mechanisms,a numerical investigation is performed for a row of cylindrical holes under some typical blowing ratios(0.5,1.0 and 1.5).The interaction features of jet-mainstream,as well as the effect of temperature ratio between the hot flow and cold flow on the film adiabatic heating or cooling effectiveness are analyzed.The results show that the jet penetration into the mainstream under the film heating scheme is more significant related to the film cooling scheme,causing the jet to lift off the surface and inducing bigger counter-rotating vortex pair downstream the film-hole.When the temperature ratio is close to 1,the film adiabatic heating effectiveness is nearly the same as the film adiabatic cooling effectiveness.However,once the temperature ratio is far deviated from 1,the difference between film adiabatic heating effectiveness and film adiabatic cooling effectiveness is behaved obviously.
To reveal the similarities and differences between film cooling and film heating in the physical mechanisms,a numerical investigation is performed for a row of cylindrical holes under some typical blowing ratios(0.5,1.0 and 1.5).The interaction features of jet-mainstream,as well as the effect of temperature ratio between the hot flow and cold flow on the film adiabatic heating or cooling effectiveness are analyzed.The results show that the jet penetration into the mainstream under the film heating scheme is more significant related to the film cooling scheme,causing the jet to lift off the surface and inducing bigger counter-rotating vortex pair downstream the film-hole.When the temperature ratio is close to 1,the film adiabatic heating effectiveness is nearly the same as the film adiabatic cooling effectiveness.However,once the temperature ratio is far deviated from 1,the difference between film adiabatic heating effectiveness and film adiabatic cooling effectiveness is behaved obviously.
引文
[1]BOGARD D G,THOLE K A.Gas turbine film cooling[J].AIAA Journal of Propulsion and Power,2006,22(2):249-270.
[2]BUNKER R S.A review of turbine shaped film cooling technology[J].ASME Journal of Heat Transfer,2005,127:441-453.
[3]LEE K D,KIM K Y.Shape optimization of a fanshaped hole to enhance film-cooling effectiveness[J].International Journal of Heat and Mass Transfer,2010,53:2996-3005.
[4]YANG C F,ZHANG J Z.Experimental investigation on film cooling characteristics from a row of holes with ridge-shaped tabs[J].Experimental Thermal and Fluid Science,2012,37:113-120.
[5]YAO Y,ZHANG J Z,WANG L P.Film cooling on agas turbine blade suction with converging slot-hole[J].International Journal of Thermal Science,2013,65:267-279.
[6]常艳,杨卫华,张靖周.突片形状对气膜冷却效率的影响[J].南京航空航天大学学报,2016,48(3):317-325.CHANG Yan,YANG Weihua,ZHANG Jingzhou.Effects of tab shapes on film cooling effectiveness[J].Journal of Nanjing University of Aeronautics and Astronautics,2016,48(3):317-325.
[7]CERRI G,GIOVANNELLI A,BATTISTI L,et al.Advances in effusive cooling techniques of gas turbines[J].Applied Thermal Engineering,2007,27:692-698.
[8]KREWINKEL R.A review of gas turbine effusion cooling studies[J].International Journal of Heat and Mass Transfer,2013,66:706-722.
[9]张靖周,周君辉,刘春丽.内冷通道横流对气膜冷却效率的影响[J].南京航空航天大学学报,2014,46(4):509-516.ZHANG Jingzhou,ZHOU Junhui,LIU Chunli.Effect of internal crossflow in coolant channel on adiabatic film cooling effectiveness[J].Journal of Nanjing University of Aeronautics and Astronautics,2014,46(4):509-516.
[10]EKKAD S V,ZAPATA D,HAN J C.Film effectiveness over a flat surface with air and CO2injection through compound angle holes using a transient liquid crystal image method[J].ASME Journal of Turbomachinery,1997,119:587-593.
[11]MICHAEL C J,BOGARD D G.Effects of coolant density ratio on film cooling performance on a vane[R].ASME Paper GT2003-38582,2003.
[12]POST J W,ACHARYA S.The role of density ratio and blowing ratio on film cooling in a vane passage[R].ASME Paper GT2010-23680,2010.
[13]李佳,任静,蒋红德.密度比和吹风比对透平静叶气膜冷却的影响[J].工程热物理学报,2011,32(8):1295-1298.LI Jia,REN Jing,JIANG Hongde.Effects of density ratio and blowing ratio on the film cooling effectiveness on a turbine vane[J].Journal of Engineering Thermophysics,2011,32(8):1295-1298.
[14]PELLISSIER M P C,HABASHI W G.Optimization via FENSAP-ICE of aircraft hot-air anti-icing systems[J].Journal of Aircraft,2011,48:265-276.
[15]马辉,陈维建,孟繁鑫,等.发动机导向叶片热气防冰腔结构改进[J].南京航空航天大学学报,2013,45(1):70-74.MA Hui,CHEN Weijian,MENG Fanxin,et al.Improvement of hot-air anti-icing structure of engine inlet vane[J].Journal of Nanjing University of Aeronautics and Astronautics,2013,45(1):70-74.
[16]高艳欣,周建军,李云单,等.吹气式旋转帽罩冰腔特性[J].南京航空航天大学学报,2016,48(3):359-365.GAO Yanxin,ZHOU Jianjun,LI Yundan,et al.Anti-icing properties of blowing rotating spinner[J].Journal of Nanjing University of Aeronautics and Astronautics,2016,48(3):359-365.
[17]PEDERSEN D R,ECKERT E R G,GOLDSTEIN R J.Film cooling with large density differences between the mainstream and the secondary fluid measured by the heat-mass transfer analogy[J].ASME Journal of Heat Transfer,1977,99:620-627.
[18]HARRISON K,BOGARD D.Comparison of RANS turbulence models for prediction of film cooling performance[R].ASME Paper GT2008-50366,2008.
[2]BUNKER R S.A review of turbine shaped film cooling technology[J].ASME Journal of Heat Transfer,2005,127:441-453.
[3]LEE K D,KIM K Y.Shape optimization of a fanshaped hole to enhance film-cooling effectiveness[J].International Journal of Heat and Mass Transfer,2010,53:2996-3005.
[4]YANG C F,ZHANG J Z.Experimental investigation on film cooling characteristics from a row of holes with ridge-shaped tabs[J].Experimental Thermal and Fluid Science,2012,37:113-120.
[5]YAO Y,ZHANG J Z,WANG L P.Film cooling on agas turbine blade suction with converging slot-hole[J].International Journal of Thermal Science,2013,65:267-279.
[6]常艳,杨卫华,张靖周.突片形状对气膜冷却效率的影响[J].南京航空航天大学学报,2016,48(3):317-325.CHANG Yan,YANG Weihua,ZHANG Jingzhou.Effects of tab shapes on film cooling effectiveness[J].Journal of Nanjing University of Aeronautics and Astronautics,2016,48(3):317-325.
[7]CERRI G,GIOVANNELLI A,BATTISTI L,et al.Advances in effusive cooling techniques of gas turbines[J].Applied Thermal Engineering,2007,27:692-698.
[8]KREWINKEL R.A review of gas turbine effusion cooling studies[J].International Journal of Heat and Mass Transfer,2013,66:706-722.
[9]张靖周,周君辉,刘春丽.内冷通道横流对气膜冷却效率的影响[J].南京航空航天大学学报,2014,46(4):509-516.ZHANG Jingzhou,ZHOU Junhui,LIU Chunli.Effect of internal crossflow in coolant channel on adiabatic film cooling effectiveness[J].Journal of Nanjing University of Aeronautics and Astronautics,2014,46(4):509-516.
[10]EKKAD S V,ZAPATA D,HAN J C.Film effectiveness over a flat surface with air and CO2injection through compound angle holes using a transient liquid crystal image method[J].ASME Journal of Turbomachinery,1997,119:587-593.
[11]MICHAEL C J,BOGARD D G.Effects of coolant density ratio on film cooling performance on a vane[R].ASME Paper GT2003-38582,2003.
[12]POST J W,ACHARYA S.The role of density ratio and blowing ratio on film cooling in a vane passage[R].ASME Paper GT2010-23680,2010.
[13]李佳,任静,蒋红德.密度比和吹风比对透平静叶气膜冷却的影响[J].工程热物理学报,2011,32(8):1295-1298.LI Jia,REN Jing,JIANG Hongde.Effects of density ratio and blowing ratio on the film cooling effectiveness on a turbine vane[J].Journal of Engineering Thermophysics,2011,32(8):1295-1298.
[14]PELLISSIER M P C,HABASHI W G.Optimization via FENSAP-ICE of aircraft hot-air anti-icing systems[J].Journal of Aircraft,2011,48:265-276.
[15]马辉,陈维建,孟繁鑫,等.发动机导向叶片热气防冰腔结构改进[J].南京航空航天大学学报,2013,45(1):70-74.MA Hui,CHEN Weijian,MENG Fanxin,et al.Improvement of hot-air anti-icing structure of engine inlet vane[J].Journal of Nanjing University of Aeronautics and Astronautics,2013,45(1):70-74.
[16]高艳欣,周建军,李云单,等.吹气式旋转帽罩冰腔特性[J].南京航空航天大学学报,2016,48(3):359-365.GAO Yanxin,ZHOU Jianjun,LI Yundan,et al.Anti-icing properties of blowing rotating spinner[J].Journal of Nanjing University of Aeronautics and Astronautics,2016,48(3):359-365.
[17]PEDERSEN D R,ECKERT E R G,GOLDSTEIN R J.Film cooling with large density differences between the mainstream and the secondary fluid measured by the heat-mass transfer analogy[J].ASME Journal of Heat Transfer,1977,99:620-627.
[18]HARRISON K,BOGARD D.Comparison of RANS turbulence models for prediction of film cooling performance[R].ASME Paper GT2008-50366,2008.