International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Experimental Study on the Film Cooling Effectiveness on a Flat Plate with Anti-Vortex Holes

  • Park, Soon Sang (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Park, Jung Shin (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kwak, Jae Su (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • Received : 2014.03.31
  • Accepted : 2014.06.26
  • Published : 2014.06.30
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Abstract

In this paper, the effects of the anti-vortex hole angle and blowing ratio on the flat plate film cooling effectiveness were experimentally investigated. For the film cooling effectiveness measurement, pressure sensitive paint technique was applied. The experiments were conducted for cylindrical and anti-vortex film cooling holes, and three blowing ratios of 0.25, 0.5, and 1.0 were tested. Two anti-vortex hole angles of 0 and 15 degree with respect to the flow direction were considered. For the cylindrical hole case, the film cooling effectiveness decreased as the blowing ratio increased because of the coolant lift-off. For the angle anti-vortex hole cases, however, higher blowing ratio resulted in higher film cooling effectiveness due to the reduced actual blowing ratio and diminished kidney vortex. For all blowing ratio, the angled anti-vortex hole case showed the highest film cooling effectiveness.

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