Effect of spherical blockage configurations on film cooling

Abstract

With increasing inlet temperature of gas turbines, turbine blades need to be effec-tively protected by using cooling technologies. However, the deposition from the fuel impurities and dust particles in the air is often found inside film holes, which results in partial hole blockage. In this paper, the deposition geometry is simpli-fied as a rectangular channel, and the effect of three blockage ratios is investi-gated by using the computational fluid dynamics. In addition, water droplets are also released from the coolant inlet to provide a comparison of the results with and without mist injection. It is found that the lateral film cooling effectiveness is reduced with increasing blockage ratio. For all the cases with the blowing ratio 0.6, 1% mist injection provides an improvement of the cooling performance by approximately 10%.