The effects on turbine blade surface pressure and aerodynamic loss distribution ofcoolantanair inject from each of three individual rows of coolant holes on the blade leading-edge, and the rear of the suction and the pressure surface were investigated in a Iinearcascade. The experimental results showed that the changes in the pressure and aerodynamicloss distribution were dependent primarily on the amount of coolant added and the locationof injecting holes. The pressure surface injection did not change the pressure distributionas clearly as did the suction surface injection due mainly to the difference of mainstreampressure gradients and velocity. The air injection from suction surface led to the largesteffect on the loss increase while the air injection from the pressure surface exerted the leastinfluence.
