Influences of position of hole-rows on film cooling heat transfer of turbine blade surface

Film cooling heat transfer of single film row at different locations on turbine blade surface was studied experimentally. A three-blade liner cascade in a large-scale low-speed opening wind tunnel was used in the experiment. There are 15 rows of film cooling holes at the surface of middle blade made of high quality wood. Three rows are on the suction surface. Six rows are on the leading edge. Six rows are on the pressure surface. Film cooling heat transfer on the blade surface is measured in the cases of blowing ratio changes from 0.5 to 2.5. Result shows that the local heat transfer coefficients with film injection are higher than that without film injection for the cases of high blowing ratio, and it is reverse for the cases of low blowing ratio. The regions of influence of film injection are different at the different location of blade.