温度比对导叶端壁冷却特性的影响
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摘要
利用高温风洞及远红外热像技术,在两种主流/冷气温度比(1.53和2.29)和3种冷气/主流质量流量比(0.50%,1.25%和1.50%)下,研究了温度比对导叶端壁综合冷却特性的影响。对比高、低温比下的实验结果发现:保持冷流温度不变,通过增加主流温度来提高温比,会使整个端壁表面冷却效率却显著增加;高温比改变了端壁表面的冷却特性,端壁不同位置冷却效率在高温比时增加的幅度不同,端壁高、低冷却效率区发生变化,适用于低温比的气膜孔布局方案可能并不适用于高温比;温比对端壁前缘冷却特性的影响较大,对端壁尾缘的影响较小。
Experimental investigations of the cooling characteristics of a vane end-wall were carried out in a hot wind tunnel using infrared thermograph technique.Two mainstream-to-coolant temperature ratios of 1.53 and 2.29,and three coolant-to-mainstream mass flow ratios of 0.50%,1.25% and 1.50% were chosen.Comparing the results obtained at high and low temperature ratio,the following three conclusions can be drawn.The experimental method of increasing the temperature ratio by increasing the mainstream temperature and keeping the coolant temperature constant led to a significant increase in the overall cooling effectiveness of the end-wall surface.The cooling characteristics of the end-wall surface changed as the temperature ratio increased.As the temperature ratio had different effect of cooling effectiveness at different positions of the end-wall,the areas with high and low cooling effectiveness changed.The scheme of hole-layout suitable for low temperature ratio may not be applicable to high temperature ratio.The effect of temperature ratio on the cooling characteristics was great at the leading edge,but not evident at the trailing edge.
Experimental investigations of the cooling characteristics of a vane end-wall were carried out in a hot wind tunnel using infrared thermograph technique.Two mainstream-to-coolant temperature ratios of 1.53 and 2.29,and three coolant-to-mainstream mass flow ratios of 0.50%,1.25% and 1.50% were chosen.Comparing the results obtained at high and low temperature ratio,the following three conclusions can be drawn.The experimental method of increasing the temperature ratio by increasing the mainstream temperature and keeping the coolant temperature constant led to a significant increase in the overall cooling effectiveness of the end-wall surface.The cooling characteristics of the end-wall surface changed as the temperature ratio increased.As the temperature ratio had different effect of cooling effectiveness at different positions of the end-wall,the areas with high and low cooling effectiveness changed.The scheme of hole-layout suitable for low temperature ratio may not be applicable to high temperature ratio.The effect of temperature ratio on the cooling characteristics was great at the leading edge,but not evident at the trailing edge.
引文
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[19]BARIGOZZI G,FRANCHINI G,PERDICHIZZI A,et al.Film cooling of a contoured endwall nozzle vane through fan-shaped holes[J].International Journal of Heat and Mass Transfer,2010,31(4):576-585.
[20]STRAUB D L,SIDWELL T G,CASLETON K H,et al.High temperature film cooling test facility and preliminary test results[R].ASME Paper GT2012-69767,2012.
[21]MONTOMOLI F,MASSINI M,YANG H,et al.The benefit of high-conductivity materials in film cooled turbine nozzles[J].International Journal of Heat and Fluid Flow,2012,34:107-116.
[22]SU H,PU J,WANG J H,et al.An experimental investigation of cooling characteristics at a vane end-wall with a locally enhanced hole-layout[J].Experimental Thermal and Fluid Science,2018,96(1):137-145.
[23]CUNHA F J,DAHMER M T,CHYU M K.Analysis of airfoil trailing edge heat transfer and its significance in thermal-mechanical design and durability[J].Journal of Turbomachinery,2006,128(4):738-746.
[24]TASLIM M E,WADSWORTH C M.An experimental investigation of the rib surface-averaged heat transfer coefficient in a rib-roughened square passage[J].Journal of Turbomachinery,1997,119(2):381-389.
[2]张扬,齐士博,袁新.涡轮流场影响端壁气膜冷却的实验研究[J].工程热物理学报,2011,32(6):941-944.ZHANG Yang,QI Shibo,YUAN Xin.Experimental investigation on the turbine blade platform film cooling effected by the flow field[J].Journal of Engineering Thermophysics,2011,32(6):941-944.(in Chinese)
[3]LI X Y,REN J,JIANG H D.Film cooling effectiveness distribution of cylindrical hole injections at different locations on a vane endwall[J].International Journal of Heat and Mass Transfer,2015,90:1-14.
[4]袁瑞明,浦健,王位,等.温比对第一级导叶端壁气膜冷却特性的影响[J].航空动力学报,2018,33(8):1872-1879.YUAN Ruiming,PU Jian,WANG Wei,et al.Experimental investigation of temperature ratio effect on film cooling characteristics at a first-stage vane end-wall[J].Journal of Aerospace Power,2018,33(8):1872-1879.(in Chinese)
[5]PU J,WANG J H,MA S Y,et al.An experimental investigation of geometric effect of upstream converging slot-hole on end-wall film cooling and secondary vortex characteristics[J].Experimental Thermal and Fluid Science,2015,69(6):58-72.
[6]LIU C,ZHU H,BAI J,et al.Film cooling performance of converging slot-hole rows on a gas turbine blade[J].International Journal of Heat and Mass Transfer,2010,53(23/24):5232-5241.
[7]YAO Y,ZHANG J Z,WANG L P.Film cooling on a gas turbine blade suction side with converging slot-hole[J].International Journal of Thermal Sciences,2013,65(3):267-279.
[8]THRIFT A A,THOLE K A,HADA S.Effects of orientation and position of the combustor-turbine interface on the cooling of a vane endwall[J].Journal of Turbomachinery,2012,134(6):291-301.
[9]THOLE K A,KNOST D G.Heat transfer and film-cooling for the endwall of a first stage turbine vane[J].International Journal of Heat and Mass Transfer,2005,48(25/26):5255-5269.
[10]CHEN A F,SHIAU C C,HAN J C.Turbine blade platform film cooling with fan-shaped holes under simulated swirl purge flow and slashface leakage conditions[J].Journal of Turbomachinery,2018,140(1):011006.1-011006.11.
[11]KOHLI A,BOGARD D G.Effects of very high free-stream turbulence on the jet-mainstream interaction in a film cooling flow[J].Journal of Turbomachinery,1998,120(4):785-790.
[12]COLETTI F,ELKINS C J,EATON J K.An inclined jet in crossflow under the effect of streamwise pressure gradients[J].Experiments in Fluids,2013,54(9):1589.1-1589.16.
[13]BALDAUF S,SCHEURLEN M,SCHULZ A,et al.Correlation of film cooling effectiveness from thermographic measurements at engine like conditions[J].Journal of Turbomachinery,2002,124(4):686-698.
[14]PIETRZYK J R,BOGARD D G,CRAWFORD M E.Effects of density ratio on the hydrodynamics of film cooling[J].Journal of Turbomachinery,1990,112(3):437-443.
[15]SATTA F,TANDA G.Measurement of local heat transfer coefficient on the endwall of a turbine blade cascade by liquid crystal thermography[J].Experimental Thermal and Fluid Science,2014,58(5):209-215.
[16]张超,王湛,周嗣京,等.压力敏感涂料的标定及在气膜冷却效率测量中的应用[J].航空动力学报,2011,26(12):2691-2697.ZHANG Chao,WANG Zhan,ZHOU Sijing,et al.Calibration of pressure sensitive paint and application to the measurement of film cooling effectiveness[J].Journal of Aerospace Power,2011,26(12):2691-2697.(in Chinese)
[17]WRIGHT L M,GAO Z H,YANG H T,et al.Film cooling effectiveness distribution on a gas turbine blade platform with inclined slot leakage and discrete film hole flows[J].Journal of Heat Transfer,2008,130(7):383-394.
[18]KUNZE M,VOGELER K,CRAWFORD M,et al.Single and multiple row endwall film-cooling of a highly loaded first turbine vane with variation of loading[J].Journal of Turbomachinery,2014,136(6):061012.1-061012.14.
[19]BARIGOZZI G,FRANCHINI G,PERDICHIZZI A,et al.Film cooling of a contoured endwall nozzle vane through fan-shaped holes[J].International Journal of Heat and Mass Transfer,2010,31(4):576-585.
[20]STRAUB D L,SIDWELL T G,CASLETON K H,et al.High temperature film cooling test facility and preliminary test results[R].ASME Paper GT2012-69767,2012.
[21]MONTOMOLI F,MASSINI M,YANG H,et al.The benefit of high-conductivity materials in film cooled turbine nozzles[J].International Journal of Heat and Fluid Flow,2012,34:107-116.
[22]SU H,PU J,WANG J H,et al.An experimental investigation of cooling characteristics at a vane end-wall with a locally enhanced hole-layout[J].Experimental Thermal and Fluid Science,2018,96(1):137-145.
[23]CUNHA F J,DAHMER M T,CHYU M K.Analysis of airfoil trailing edge heat transfer and its significance in thermal-mechanical design and durability[J].Journal of Turbomachinery,2006,128(4):738-746.
[24]TASLIM M E,WADSWORTH C M.An experimental investigation of the rib surface-averaged heat transfer coefficient in a rib-roughened square passage[J].Journal of Turbomachinery,1997,119(2):381-389.