An experimental investigation has been performed tomeasure the film cooling performance of louver scheme over ascaled vane of high-pressure gas turbine using a twodimensionalcascade. Two rows of axially oriented louverscheme are used to cool the suction side and their performanceis compared with two similar rows of standard cylindricalholes. The effect of hole location on the cooling performanceis investigated for each row individually, then the rowinteraction is investigated for both rows at four differentblowing ratios ranging from 1 to 2 with a 0.9 density ratio.The exit Reynolds number based on the true chord is 1.5E5and exit Mach number is 0.23. The temperature distribution onthe vane is mapped using a transient Thermochromic LiquidCrystal (TLC) technique to obtain the local distributions of theheat transfer coefficient and film cooling effectiveness. Thelouver scheme shows a superior cooling effectiveness thanthat of the cylindrical holes at all blowing ratios in terms ofprotection and lateral coverage. The row location highlyaffects the cooling performance for both the louver andcylindrical scheme.