Detailed experimental study on film cooling effect of one enlarged model of turbine blade leading edge cooling structure was carried out. The surface temperature distribution of blade was captured by the infrared radiation camera. The influence of adiabatic cooling efficiency and pressure loss were analyzed by different film angles of leading edge

blow ratios

main flow Reynolds numbers. In the experiment

the range of three-row film angle on leading edge was 35 degree to 90 degree; the range of main flow Reynolds number was 76112-142624

and the range of blow ratio was 0.44-2.64. The results show that: the film cooling on the stagnation region of leading edge is getting better with the decrease of film angle; the pressure loss coefficient is lowest with film angle of 45 degree and highest with film angle of 75 degree; with increase of main flow Reynolds number

the adiabatic cooling efficiency decreases

and the pressure loss coefficient increases; the adiabatic cooling efficiency reaches to the maximum when blow ratio increases to 1.32 and then decreases when blow ratio keeps increasing.