Influence of Coolant Density on Turbine Blade Film Cooling With Axial and Compound Shaped Holes

Abstract

Adiabatic filmcooling effectiveness is examined systematically on a typical high pressure turbine blade by varying three critical flow parameters: coolant blowing ratio, coolanttomainstream density ratio, and freestream turbulence intensity. Three coolant density ratios 1.0, 1.5, and 2.0 are chosen for this study. The average blowing ration and the turbulence intensity are 1.5% and 10.5%, respectively. Conductionfree pressure sensitive paint (PSP) technique is used to measure filmcooling effectiveness. Foreign gases are used to study the effect of coolant density. Two test blades feature axial angle and 45 deg compoundangle shaped holes on the suction side and pressure side. Both designs have 3 rows of 30 deg radialangle cylindrical holes around the leading edge region. The inlet and the exit Mach number are 0.27 and 0.44, respectively. Reynolds number based on the exit velocity and blade axial chord length is 750,000. Overall, the compound angle design performs better film coverage that axial angle. Greater coolanttomainstream density ratio results in lower coolanttomainstream momentum and prevents coolant to liftoff.