B-11 タービン翼前縁付け根部のフィルム冷却が馬蹄渦形成に及ぼす影響(伝熱,一般講演)

概要

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Film cooling is one of today's most effective ways to protect endwall and vane surfaces from high temperature combustion gas. This study looks at the effect of endwall film cooling at the junction of a first stage nozzle guide vane where complex vortex patterns including a Horseshoe Vortex are known to exist. This experiment has been simulated by using a single symmetrical airfoil with a single shaped cooling hole on the endwall in front of the airfoil. Experimental techniques such as Pressure Sensitive Paint (PSP), Laser Induced Fluorescence (LIF), and Particle Image Velocimetry (PIV) were used to determine the film cooling effectiveness and to visualize the flow fields at the junction of the leading edge with varying the distance between the airfoil and cooling hole, and the mass flow ratio,. In conclusion, this study shows the effectiveness of the endwall film cooling for the suppression of horseshoe vortex formation, and the mechanisms of the suppression.
公益社団法人日本ガスタービン学会の論文
2011-07-06