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THE EFFECT OF EMBEDDED VORTICES ON FILM COOLING WITH COMPOUND ANGLE ORIENTATIONS

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.560
13 pages

Hyo Kyung Chung
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-744, Korea

Young Su Na
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-744, Korea

Joon Sik Lee
School of Mechanical and Aerospace Engineering, Seoul National University, San 56-1. Sillim-dong Gwanak-gu. Seoul 151-742 Korea

Résumé

Present study figures out the effect of embedded vortices on film cooling with compound angle of inclination and orientations. The inclination angle of the cooling hole is fixed at 35°, and two orientation angles, 0° and 60° are investigated. The blowing ratios of injected coolant to mainstream are 0.5, 1.0, and 2.0. Four relative positions of vortices with respect to film cooling holes are investigated. For compound angle, the effect of rotational directions of vortices is also observed. Distributions of adiabatic film cooling effectiveness and heat transfer coefficient ratio are measured using thermochromic liquid crystal technique. Results show that distributions of local adiabatic effectiveness and heat transfer coefficient ratio vary remarkably according to the relative positions of vortices and rotational directions. The compound angle injection provides the higher film cooling effectiveness and more uniform distribution compared to the simple angle injection without orientation angle. As the blowing ratio increases, the heat transfer coefficient varies remarkably according to the relative positions of the vortex due to the effect of the secondary flow, and is greatly affected by the rotational directions.

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