Abstract: Film cooling effectiveness of hole rows on leading edge of turbine blade has been studied experimentally. The model is a blunt body with a half cylinder leading edge with two flat side walls. Six rows of round holes were ungradatedly located at ±15°,±40° and ±60° from stagnation on the half cylinder leading edge. The holes in each row were spaced three hole diameters apart and were angled 30° and 90° to the surface in the spanwise and streamwise directions respectively. The length of hole is four hole diameters. The focus of this paper is the influences of holes row position on film cooling effectiveness on leading edge of turbine blade. Measurement was carried out for mainstream Reynolds number (based on leading edge diameter) from 42000 to 127000 and blowing ratio (average secondary to mainstream mass flux ratio) from 0.5 to 2.0. The results show that the better position of single holes row ordinally is 60°, 40°and 15°, and that the better position of double holes row is (40°,60°). The results also show that there is no difference in using single or double or three film cooling holes row with larger secondary flow flux, and that the better film cooling effect with smaller secondary flow flux can be taken in using three film cooling holes row.

Key words: leading edge of blade, film coo ling effect iveness, ho le-row s