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 (, 1.7, and 2.2 on the pressure side and , 1.4, and 1.8 on the suction side), three average coolant density ratios (, 1.5, and 2.5), and two average freestream turbulence intensities ( and 10.5%) are considered. Conduction-free pressure sensitive paint (PSP) technique is adopted to measure film-cooling effectiveness. Three foreign gases— for low density, for medium density, and a mixture of 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 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, . Higher freestream turbulence causes effectiveness to drop everywhere except in the region downstream of the suction side where significant improvement in effectiveness is seen.
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Research Papers
Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique
Diganta P. Narzary
,
Diganta P. Narzary
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
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Kuo-Chun Liu
,
Kuo-Chun Liu
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
Akhilesh P. Rallabandi
,
Akhilesh P. Rallabandi
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
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Je-Chin Han
Je-Chin Han
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
jc-han@tamu.edu
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
Diganta P. Narzary
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
Kuo-Chun Liu
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
Akhilesh P. Rallabandi
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123
Je-Chin Han
Department of Mechanical Engineering, Turbine Heat Transfer Laboratory,
Texas A&M University
, College Station, TX 77843-3123jc-han@tamu.edu
J. Turbomach. May 2012, 134(3): 031006 (10 pages)
Published Online: July 14, 2011
Article history
Received:
July 3, 2010
Revised:
July 7, 2010
Online:
July 14, 2011
Published:
July 14, 2011
Citation
Narzary, D. P., Liu, K., Rallabandi, A. P., and Han, J. (July 14, 2011). "Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique." ASME. J. Turbomach. May 2012; 134(3): 031006. https://doi.org/10.1115/1.4003025
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