基于PSP实验技术的双射流气膜冷却 特性研究

韩昌; 李佳; 李雪英; 任静; 蒋洪德

基于PSP实验技术的双射流气膜冷却特性研究

清华大学机械工程学院热能工程系燃气轮机研究中心,北京 100084

基金项目: 国家重点基础研究发展计划(2007CB210100)

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出版历程
- 收稿日期: 2009-11-09
- 修回日期: 2010-05-17
- 刊出日期: 2010-12-28

Characteristic of double-jet film cooling tested by pressure sensitive paint

Gas Turbine Research Center,Department of Thermal Engineering, School of Mechanical Engineering,Tsinghua University,Beijing 100084,China

摘要

摘要: 基于压力敏感漆(PSP)实验技术研究了具有双射流、圆孔和扇形孔的气膜冷却系统在主流湍流度为6%,吹风比分别为0.5,0.8,1.0,1.2和1.5时的冷却特性.圆孔平均气膜冷却效率在吹风比为0.8到1.5范围内逐渐降低;而双射流和扇形孔在整个实验范围内随吹风比的增大而升高,这表明双射流很好地抑制了射流与壁面的吹离.在同等条件下,双射流气膜冷却效率优于圆孔,而低于扇形孔.实验条件下的数值模拟结果清楚地表明了圆孔、双射流和扇形孔分别形成的肾形涡系、反肾形涡系和弱肾形涡系是形成各自气膜冷却特性的主要因素.
- 燃气轮机 /
- 气膜冷却 /
- 双射流 /
- 压力敏感漆 /
- 反肾形涡
Abstract: The characteristics of the film cooling system with double-jet,round and shaped holes were investigated under the condition of mainstream turbulence 6% and blowing ratio 0.5,0.8,1.0,1.2,1.5 in the study.The pressure sensitive paint (PSP) was implemented in the tests as the main measurement technique.The film cooling effectiveness decreases between blowing ratio 0.8 and 1.5 in the case of round holes,but increases in the whole experimental blowing ratio in the case of shaped holes and double-jet.It indicates that the double-jet restrains the lift-off of the cooling jet.The film cooling effectiveness of double-jet is better than that of the round holes,but poor than that of the shaped holes in the same conditions.Meanwhile,the vortex structures near the three focused holes obtained from the corresponding computations are major causes of the characteristics of the investigated film cooling systems.
- gas turbine /
- film cooling /
- double-jet /
- pressure sensitive paint (PSP) /

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参考文献(19)

[1]	Goldstein R J.Film cooling[M]//Irvine T F.Advances in Heat Transfer,1971:321-379.
[2]	Han J C,Dutta S E.Gas turbine heat transfer and cooling technology [M].New York:Taylor & Francis,2000.
[3]	Goldstein R J.Film cooling following injection through inclined circular tubes .NASA CR-72612,1969.
[4]	Leylek J H,Zerkle R D.Discrete-jet film cooling:a comparison of computational results with experiments [J].ASME Journal of Turbomachinery,1994,116(3):358-368.
[5]	Walters D K,Leylek J H.Detailed analysis of film-cooling physics:Part Ⅰ—Streamwise injection with cylindrical holes //Proceedings of the 1997 International Gas Turbine & Aeroengine Congress & Exposition.New York,NY,United States:ASME,1997.
[6]	Goldstein R J,Eckert E R G,Burggraf F.Effects of hole geometry and density on three-dimensional film cooling[J].International Journal of Heat and Mass Transfer,1974,17(5):595-607.
[7]	Mhetras S,Han J C,Rudolph R.Film-cooling effectiveness from shaped film cooling holes for a gas turbine blade .ASME GT-2008-50916,2008.
[8]	Colban W,Thole K A,Haendler M.A comparison of cylindrical and fan-shaped film-cooling holes on a vane endwall at low and high freestream turbulence levels[J].ASME Journal of Turbomachinery,2008,130(7):60-68.
[9]	Saumweber C,Schul A,Witting S.Free stream turbulence effects on film cooling with shaped holes .Amsterdam:IGTI Turbo Expo,GT-2002-30170,2002.
[10]	Bunker R S.A review of shaped hole turbine film cooling technology[J].ASME Journal of Heat Transfer,2005,127(4):441-453.
[11]	Goldstein R J,Jin P.Film cooling downstream of a row of discrete holes with compound angle [J].ASME Journal of Turbomachinery,2001,123(2):222-230.
[12]	McGovern K T,Leylek J H.A detailed analysis of film cooling physics:Part Ⅱ—Compound-angle injection with cylindrical holes[J].ASME Journal of Turbomachinery,2000,122(1):113-121.
[13]	ZHANG Luzeng,YIN Juan,Moon H K.The effect of compound angle on nozzle pressure side film cooling .ASME GT2009-59141,2009.
[14]	Kusterer K,Bohn D,Sugimoto T.Double-jet ejection of cooling air for improved film-cooling .ASME GT2006-90854,2006.
[15]	Kusterer K,Bohn D,Sugimoto T.Influence of blowing ratio on the double-jet ejection of cooling air[J].ASME Turbo Expo,GT2007-27301,2007.
[16]	Morris M J,Donovan J F,Kegelman J T,et al.Aerodynamic applications of pressure sensitive paint .AIAA 92-0264,1992.
[17]	Zhang L Z,Baltz M,Padupatty R.Turbine nozzle film cooling study using the pressure sensitive paint (PSP) technique .ASME 99-GT-196,1999.
[18]	Ahn J,Mhetras S,Han J C.Film-cooling effectiveness on a gas turbine blade tip using pressure sensitive paint .ASME GT2004-53249,2004.
[19]	Mhetras S,YANG Huitao,GAO Zhihong,et al.Film-cooling effectiveness on squealer rim walls and squealer cavity floor of a gas turbine blade tip using pressure sensitive paint .ASME GT2005-68387,2005.