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Heat Transfer Research
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ISSN Imprimer: 1064-2285
ISSN En ligne: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.2016012457
pages 557-570

EFFECT OF ANTI-VORTEX HOLE ANGLE ON THE FILM COOLING EFFECTIVENESS

Soon Sang Park
School of Aerospace and Mechanical Engineering, Korea Aerospace University, Korea
Younggi Moon
School of Aerospace and Mechanical Engineering, Korea Aerospace University, Korea
Jung Shin Park
School of Aerospace and Mechanical Engineering, Korea Aerospace University, Korea
Jae Su Kwak
School of Aerospace and Mechanical Engineering, Korea Aerospace University, Korea

RÉSUMÉ

The effects of the anti-vortex hole angle and blowing ratio on the flat plate film cooling effectiveness were investigated experimentally. To measure the cooling effectiveness of the film, a pressure sensitive paint technique was applied. The experiments were conducted for cylindrical and anti-vortex film cooling holes, and three blowing ratios: 0.25, 0.5, and 1.0. The coolant to mainstream density ratio was 1, and two anti-vortex hole angles − 0° and 15° − with respect to the flow direction were considered. For the cylindrical hole case, the film cooling effectiveness decreased with the rising blowing ratio because of the coolant lift-off. For the 15° anti-vortex hole case, however, a higher blowing ratio resulted in greater film cooling effectiveness due to the reduced actual blowing ratio and diminished kidney vortex. For all blowing ratios, the 15° anti-vortex hole case showed a higher film cooling effectiveness than the 0° anti-vortex hole or the cylindrical hole case.


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