터빈블레이드 흡입면에서의 막냉각 효율에 냉각홀 확장각이 미치는 영향

The nozzle shape effect on a film cooling system of a turbine blade suction surface was experimentally investigated. Liquid crystal with hue-temperature correlation and an image processing system were employed to evaluate surface temperature. Cooling effectiveness on both of suction surface was presented. It was found that the averaged cooling efficiency on the suction surface was maximum with 10 degree of the cooling hole expansion angle.