扰流柱布局对网格缝结构气膜冷却特性的影响
|
摘要
为了研究网格缝结构的气膜冷却特性,开展了平板模型试验研究,使用瞬态液晶测温技术测量了缝下游表面的气膜冷却效率和换热系数分布,在相同压比下与圆柱孔进行了气膜冷效对比,同时研究了缝内扰流柱布局对网格缝结构气膜冷却特性的影响。网格缝结构的吹风比范围为0.26扰流柱和缝后斜面的作用下,缝下游会形成对卷旋涡,使得最下游一排扰流柱下游的气膜冷效相对较高;扰流柱顺排时,缝下游气膜冷效分布更均匀,大吹风比时,顺排结构的展向平均气膜冷效比叉排结构高出23%~84%,换热系数比高出11%;吹风比M<1时,顺排结构的流量系数更高,M>1时,叉排结构的流量系数更高。
The flat plate experimental investigations have been conducted to study the film cooling characteristics of mesh-fed slot configuration. The film cooling effectiveness and heat transfer coefficient distribution downstream the slot were measured by the transient thermal liquid crystal technique. The film cooling effectiveness of the mesh-fed slot was compared with the cylindrical hole in the condition of same pressure ratio. Meanwhile, the effect of the in-wall pin-fin arrangement on the film cooing characteristics of the mesh-fed slot was also investigated. The blowing ratio of the mesh-fed slot ranged form 0.26 to 1.25. The results show that the film cooling effectiveness laterally distribution of the mesh-fed slot is more uniform than the cylindrical hole, the jet lift-off didn't appear in the mesh-fed slot configuration when the blowing ratio increased. The counter-rotating vorticities are induced by the appendence of pin-fins and inclined plane downstream the slot. They make the film cooling effectiveness higher in the region of the downstream of the last row of pin-fin. The in-line pin-fin arrangement provides more uniform film cooling effectiveness distribution downstream the slot. At high blowing ratio, the laterally averaged film cooling effectiveness of the in-line configuration is 23%-84% higher than the staggered configuration, and the ratio of heat transfer coefficient is 11% higher. When the blowing ratio is less than 1, the discharge coefficient of in-line configuration is higher;and when the blowing ratio is more than 1, the discharge coefficient of staggered configuration is higher.
The flat plate experimental investigations have been conducted to study the film cooling characteristics of mesh-fed slot configuration. The film cooling effectiveness and heat transfer coefficient distribution downstream the slot were measured by the transient thermal liquid crystal technique. The film cooling effectiveness of the mesh-fed slot was compared with the cylindrical hole in the condition of same pressure ratio. Meanwhile, the effect of the in-wall pin-fin arrangement on the film cooing characteristics of the mesh-fed slot was also investigated. The blowing ratio of the mesh-fed slot ranged form 0.26 to 1.25. The results show that the film cooling effectiveness laterally distribution of the mesh-fed slot is more uniform than the cylindrical hole, the jet lift-off didn't appear in the mesh-fed slot configuration when the blowing ratio increased. The counter-rotating vorticities are induced by the appendence of pin-fins and inclined plane downstream the slot. They make the film cooling effectiveness higher in the region of the downstream of the last row of pin-fin. The in-line pin-fin arrangement provides more uniform film cooling effectiveness distribution downstream the slot. At high blowing ratio, the laterally averaged film cooling effectiveness of the in-line configuration is 23%-84% higher than the staggered configuration, and the ratio of heat transfer coefficient is 11% higher. When the blowing ratio is less than 1, the discharge coefficient of in-line configuration is higher;and when the blowing ratio is more than 1, the discharge coefficient of staggered configuration is higher.
引文
[1]Goldstein R J,Eckert E R,Burggraf F.Effects of Hole Geometry and Density on Three-Dimensional Film Cooling[J].International Journal of Heat Mass Transfer,1974,17:595-607
[2]Bunker R S.A Review of Shaped Hole Turbine Film Cooling Technology[J].Journal of Heat Transfer,2005,127(4):441-453
[3]Wieghardt K.Hot Air Discharge for De-Icing[R].AAF Translation Report No.F-TS-919-RE,1946:1-44
[4]Seban R A.Heat Transfer and Effectiveness for A Turbulent Boundary Layer with Tangential Fluid Injection[J].Journal of Heat Transfer,1960,32:303-312
[5]Kacker S C,Whitelaw J H.An Experimental Investigation of the Influence of Slot-Lip-Thickness on the Impervious Wall Effectiveness of the Uniform Density Two Dimensional Wall Jet[J].International Journal of Heat&Mass Transfer,1969,12(9):1196-1201
[6]Hyams D G,Mcgovern K T,Leylek J H.Effects of Geometry on Slot-Jet Film Cooling Performance[C]//Proceedings of the 1996 ASME Turbo Expo.New York,USA:ASME,96-GT-187
[7]Bayraktar S,Yilmaz T.Two-Dimensional Numerical Investigation of Film Cooling by A Cool Jet Injected at Various Angles For Different Blowing Ratios[J].Journal of Mechanical Engineering Science,2008,222(7):1215-1224
[8]Schulz A.Combustor Liner Cooling Technology in Scope of Reduced Pollutant Formation and Rising Thermal Efficiencies[J].Annals of the New York Academy of Sciences,2001,934(1):135-146
[9]杜昆,李军,晏鑫.槽缝射流对静叶端壁冷却性能的影响[J].西安交通大学学报,2015,49(1):21-26DU Kun,LI Jun,YAN Xin.Effect of the Slot Jet Impingement on the Cooling Performance of the Vane Endwall[J].Journal of Xi'an Jiaotong University,2015,49(1):21-26
[10]Waye S K,Bogard D G.High Resolution of Film Cooling Effectiveness Measurements of Axial Holes Embedded in A Transverse Trench with Various Trench Configurations[J].Journal of Turbomachinery,2007,129:294-302
[11]YUAN Hepeng,ZHU Huiren,KONG Manzhao.Effects of Blowing Ratio Measured by Liquid Crystal on Heat Transfer Characteristics of Trailing Edge Cutback[J].Chinese Journal of Aeronautics,2008,21(6):488-495
[12]Fiala N J,Johnson J D,Ames F E.Aerodynamics of A Letterbox Trailing Edge:Effects of Blowing Rate,Reynolds Number,and External Turbulence on Aerodynamic Losses and Pressure Distribution[J].Journal of Turbomachinery,2010,132(4):041011
[13]Bunker R S.A Study of Mesh-Fed Slot Film Cooling[J].Journal of Turbomachinery,2011,133(1):011022
[14]全栋梁,刘松龄,李江海,等.层板冷却特性的实验与数值模拟研究[J].推进技术,2004,25(2):134-138QUAN Dongliang,LIU Songling,LI Jianghai,et al.Experimental and Numerical Investigation of the Cooling Characteristics in A Laminate Porous Plate[J].Journal of Propulsion Technology,2004,25(2):134-138
[15]Drost U,Bolcs A,Hoffs A.Utilization of the Transient Liquid Crystal Technique for Film Cooling Effectiveness and Heat Transfer Investigations on A Flat Plane and A Turbine Airfoil[C]//Proceedings of the 1997 ASME Turbo Expo.New York,USA:ASME,97-GT-026
[16]LIU Cunliang,ZHU Huiren,BAI Jiangtao,et al.Film Cooling Performance of Converging-Slot Holes with Different Exit-Entry Area Ratios[J].Journal of Turbomachinery,2011,133:011020
[17]白江涛,朱惠人,刘存良.双参数传热实验的液晶瞬态测量不确定度分析[J].航空动力学报,2004,24(9):1945-1951BAI Jiangtao,ZHU Huiren,LIU Cunliang.Analysis of Uncertainties in Two Parameter Transient Heat Transfer Measurements with Liquid Crystal[J].Journal of Aerospace Power,2004,24(9):1945-1951
[18]Wright L M,McClain S T,Clemenson M D.Effect of Density Ratio on Flat Plate Film Cooling With Shaped Holes Using PSP[J].Journal of Turbomachinery,2011,133:041011
[2]Bunker R S.A Review of Shaped Hole Turbine Film Cooling Technology[J].Journal of Heat Transfer,2005,127(4):441-453
[3]Wieghardt K.Hot Air Discharge for De-Icing[R].AAF Translation Report No.F-TS-919-RE,1946:1-44
[4]Seban R A.Heat Transfer and Effectiveness for A Turbulent Boundary Layer with Tangential Fluid Injection[J].Journal of Heat Transfer,1960,32:303-312
[5]Kacker S C,Whitelaw J H.An Experimental Investigation of the Influence of Slot-Lip-Thickness on the Impervious Wall Effectiveness of the Uniform Density Two Dimensional Wall Jet[J].International Journal of Heat&Mass Transfer,1969,12(9):1196-1201
[6]Hyams D G,Mcgovern K T,Leylek J H.Effects of Geometry on Slot-Jet Film Cooling Performance[C]//Proceedings of the 1996 ASME Turbo Expo.New York,USA:ASME,96-GT-187
[7]Bayraktar S,Yilmaz T.Two-Dimensional Numerical Investigation of Film Cooling by A Cool Jet Injected at Various Angles For Different Blowing Ratios[J].Journal of Mechanical Engineering Science,2008,222(7):1215-1224
[8]Schulz A.Combustor Liner Cooling Technology in Scope of Reduced Pollutant Formation and Rising Thermal Efficiencies[J].Annals of the New York Academy of Sciences,2001,934(1):135-146
[9]杜昆,李军,晏鑫.槽缝射流对静叶端壁冷却性能的影响[J].西安交通大学学报,2015,49(1):21-26DU Kun,LI Jun,YAN Xin.Effect of the Slot Jet Impingement on the Cooling Performance of the Vane Endwall[J].Journal of Xi'an Jiaotong University,2015,49(1):21-26
[10]Waye S K,Bogard D G.High Resolution of Film Cooling Effectiveness Measurements of Axial Holes Embedded in A Transverse Trench with Various Trench Configurations[J].Journal of Turbomachinery,2007,129:294-302
[11]YUAN Hepeng,ZHU Huiren,KONG Manzhao.Effects of Blowing Ratio Measured by Liquid Crystal on Heat Transfer Characteristics of Trailing Edge Cutback[J].Chinese Journal of Aeronautics,2008,21(6):488-495
[12]Fiala N J,Johnson J D,Ames F E.Aerodynamics of A Letterbox Trailing Edge:Effects of Blowing Rate,Reynolds Number,and External Turbulence on Aerodynamic Losses and Pressure Distribution[J].Journal of Turbomachinery,2010,132(4):041011
[13]Bunker R S.A Study of Mesh-Fed Slot Film Cooling[J].Journal of Turbomachinery,2011,133(1):011022
[14]全栋梁,刘松龄,李江海,等.层板冷却特性的实验与数值模拟研究[J].推进技术,2004,25(2):134-138QUAN Dongliang,LIU Songling,LI Jianghai,et al.Experimental and Numerical Investigation of the Cooling Characteristics in A Laminate Porous Plate[J].Journal of Propulsion Technology,2004,25(2):134-138
[15]Drost U,Bolcs A,Hoffs A.Utilization of the Transient Liquid Crystal Technique for Film Cooling Effectiveness and Heat Transfer Investigations on A Flat Plane and A Turbine Airfoil[C]//Proceedings of the 1997 ASME Turbo Expo.New York,USA:ASME,97-GT-026
[16]LIU Cunliang,ZHU Huiren,BAI Jiangtao,et al.Film Cooling Performance of Converging-Slot Holes with Different Exit-Entry Area Ratios[J].Journal of Turbomachinery,2011,133:011020
[17]白江涛,朱惠人,刘存良.双参数传热实验的液晶瞬态测量不确定度分析[J].航空动力学报,2004,24(9):1945-1951BAI Jiangtao,ZHU Huiren,LIU Cunliang.Analysis of Uncertainties in Two Parameter Transient Heat Transfer Measurements with Liquid Crystal[J].Journal of Aerospace Power,2004,24(9):1945-1951
[18]Wright L M,McClain S T,Clemenson M D.Effect of Density Ratio on Flat Plate Film Cooling With Shaped Holes Using PSP[J].Journal of Turbomachinery,2011,133:041011