Investigations Into Film Cooling and Heat Transfer Performance on Winglet-Squealer Tips in a Turbine Stage
Film cooling and heat transfer performance on the winglet-squealer tip of a turbine stage with internal cooling channels were numerically investigated under engine condition.The effects of tip geometry and blowing ratio on the heat transfer coefficient and film cooling effectiveness distributions on the squealer tip were analyzed.The results showed that the existence of pressure-side winglet is able to eliminate the scrapping vortex in tip gap,thus improving the uniformity of coolant coverage on the squealer cavity floor.Compared to the conventional squealer tip,the area-averaged heat transfer coefficient is reduced by 11.11％and the area-averaged film cooling effectiveness is increased by 4.54％for the pressure side winglet-squealer tip.As the blowing ratio increases from 1.0 to 2.0,the area-averaged heat transfer coefficient on the winglet-squealer tip is reduced by 48.96％,and the area-averaged film cooling effectiveness on the winglet-squealer tip is improved by 154.01％.
squealer tipwingletheat transferfilm coolingblowing ratio
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