This paper is focused on the effect of film-hole configurations on platform film cooling. The platform is cooled by purge flow from a simulated stator-rotor seal combined with discrete-hole film cooling within the blade passage. The cylindrical holes and laidback fan-shaped holes are assessed in terms of film-cooling effectiveness and total pressure loss. Lined up with the freestream streamwise direction, the film holes are arranged on the platform with two different layouts. In one layout, the film-cooling holes are divided into two rows and more concentrated on the pressure side of the passage. In the other layout, the film-cooling holes are divided into four rows and loosely distributed on the platform. Four film-cooling hole configurations are investigated totally. Testing was done in a five-blade cascade with medium high Mach number condition (0.27 and 0.44 at the inlet and the exit, respectively). The detailed film-cooling effectiveness distributions on the platform were obtained using pressure sensitive paint technique. Results show that the combined cooling scheme (slot purge flow cooling combined with discrete-hole film cooling) is able to provide full film coverage on the platform. The shaped holes present higher film-cooling effectiveness and wider film coverage than the cylindrical holes, particularly at higher blowing ratios. The hole layout affects the local film-cooling effectiveness. The shaped holes also show the advantage over the cylindrical holes with lower total pressure loss.
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October 2009
Research Papers
Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling
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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Diganta Narzary,
Diganta Narzary
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,
e-mail: jc-han@tamu.edu
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
Diganta Narzary
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 77843-3123e-mail: jc-han@tamu.edu
J. Turbomach. Oct 2009, 131(4): 041004 (11 pages)
Published Online: July 1, 2009
Article history
Received:
August 18, 2008
Revised:
August 29, 2008
Published:
July 1, 2009
Citation
Gao, Z., Narzary, D., and Han, J. (July 1, 2009). "Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling." ASME. J. Turbomach. October 2009; 131(4): 041004. https://doi.org/10.1115/1.3068327
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