The effect of film-hole geometry and angle on turbine blade leading edge film cooling has been experimentally studied using the pressure sensitive paint technique. The leading edge is modeled by a blunt body with a semicylinder and an after-body. Two film cooling designs are considered: a heavily film cooled leading edge featured with seven rows of film cooling holes and a moderately film cooled leading edge with three rows. For the seven-row design, the film holes are located at 0 deg (stagnation line), ±15 deg, ±30 deg, and ±45 deg on the model surface. For the three-row design, the film holes are located at 0 deg and ±30 deg. Four different film cooling hole configurations are applied to each design: radial angle cylindrical holes, compound angle cylindrical holes, radial angle shaped holes, and compound angle shaped holes. Testing was done in a low speed wind tunnel. The Reynolds number, based on mainstream velocity and diameter of the cylinder, is 100,900. The mainstream turbulence intensity is about 7% near of leading edge model and the turbulence integral length scale is about 1.5 cm. Five averaged blowing ratios are tested ranging from to . The results show that the shaped holes provide higher film cooling effectiveness than the cylindrical holes, particularly at higher average blowing ratios. The radial angle holes give better effectiveness than the compound angle holes at . The seven-row film cooling design results in much higher effectiveness on the leading edge region than the three-row design at the same average blowing ratio or same amount coolant flow.
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June 2009
Research Papers
Influence of Film-Hole Shape and Angle on Showerhead Film Cooling Using PSP Technique
Zhihong Gao,
Zhihong Gao
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,
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
Zhihong Gao
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 77843-3123J. Heat Transfer. Jun 2009, 131(6): 061701 (11 pages)
Published Online: March 30, 2009
Article history
Received:
June 4, 2007
Revised:
December 4, 2008
Published:
March 30, 2009
Citation
Gao, Z., and Han, J. (March 30, 2009). "Influence of Film-Hole Shape and Angle on Showerhead Film Cooling Using PSP Technique." ASME. J. Heat Transfer. June 2009; 131(6): 061701. https://doi.org/10.1115/1.3082413
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