Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique

被引:85
作者
Narzary, Diganta P. [1 ]
Liu, Kuo-Chun [1 ]
Rallabandi, Akhilesh P. [1 ]
Han, Je-Chin [1 ]
机构
[1] Texas A&M Univ, Turbine Heat Transfer Lab, Dept Mech Engn, College Stn, TX 77843 USA
来源
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME | 2012年 / 134卷 / 03期
关键词
HEAT-TRANSFER; SUCTION SIDE; HOLES;
D O I
10.1115/1.4003025
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
Adiabatic film-cooling effectiveness is examined on a high-pressure turbine blade by varying three critical engine parameters, viz., coolant blowing ratio, coolant-to-mainstream density ratio, and freestream turbulence intensity. Three average coolant blowing ratios (BR = 1.2, 1.7, and 2.2 on the pressure side and BR = 1.1, 1.4, and 1.8 on the suction side), three average coolant density ratios (DR = 1.0, 1.5, and 2.5), and two average freestream turbulence intensities (Tu = 4.2% and 10.5%) are considered. Conduction-free pressure sensitive paint (PSP) technique is adopted to measure film-cooling effectiveness. Three foreign gases-N-2 for low density, CO2 for medium density, and a mixture of SF6 and argon for high density are selected to study the effect of coolant density. The test blade features two rows of cylindrical film-cooling holes on the suction side (45 deg compound), 4 rows on the pressure side (45 deg compound) and 3 around the leading edge (30 deg radial). The inlet and the exit Mach numbers are 0.24 and 0.44, respectively. The Reynolds number of the mainstream flow is 7.5 x 10(5) based on the exit velocity and blade chord length. Results suggest that the PSP is a powerful technique capable of producing clear and detailed film-effectiveness contours with diverse foreign gases. Large improvement on the pressure side and moderate improvement on the suction side effectiveness is witnessed when blowing ratio is raised from 1.2 to 1.7 and 1.1 to 1.4, respectively. No major improvement is seen thereafter with the downstream half of the suction side showing drop in effectiveness. The effect of increasing coolant density is to increase effectiveness everywhere on the pressure surface and suction surface except for the small region on the suction side, x(ss)/C-x <0.2. Higher freestream turbulence causes effectiveness to drop everywhere except in the region downstream of the suction side where significant improvement in effectiveness is seen. [DOI: 10.1115/1.4003025]
引用
收藏
页数:10
相关论文
共 25 条
[1]  
Baines W.D., 1951, Transactions of ASME, V73, P467
[2]   Gas turbine film cooling [J].
Bogard, DG ;
Thole, KA .
JOURNAL OF PROPULSION AND POWER, 2006, 22 (02) :249-270
[3]   A review of shaped hole turbine film-cooling technology [J].
Bunker, RS .
JOURNAL OF HEAT TRANSFER-TRANSACTIONS OF THE ASME, 2005, 127 (04) :441-453
[4]  
Charbonnier D., 2009, ASME Paper No. GT2009-60306
[5]  
Coleman H. W., 1989, EXPT UNCERTAINTY ANA
[6]  
Drost U., 1997, 97GT26 ASME
[7]   Combined effect of grid turbulence and unsteady wake on film effectiveness and heat transfer coefficient of a gas turbine blade with air and CO2 film injection [J].
Ekkad, SV ;
Mehendale, AB ;
Han, JC ;
Lee, CP .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1997, 119 (03) :594-600
[8]   Scaling of performance for varying density ratio coolants on an airfoil with strong curvature and pressure gradient effects [J].
Ethridge, MI ;
Cutbirth, JM ;
Bogard, DG .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2001, 123 (02) :231-237
[9]   Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes [J].
Gao, Zhihong ;
Narzary, Diganta P. ;
Han, Je-Chin .
INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER, 2008, 51 (9-10) :2139-2152
[10]   Full-coverage film cooling for a turbine blade with axial-shaped holes [J].
Gao, Zhihong ;
Narzary, Diganta P. ;
Mhetras, Shantanu ;
Han, Je-Chin .
JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 2008, 22 (01) :50-61