The standard k-εturbulence model and the SIMPLE algorithm were applied to simulate the wake produced by static blade of gas turbine

through a cylinder with diameter of 2mm

4mm and 6mm.The heat transfer characteristics on surface of the rotor blade with the angle between the injection hole centerline and the blade surface of 30°

45°and 60°were analyzed

when the dip angle within a cycle is 45°.The results show that

the Nusselt number on the rotor blade surface is different during a cycle.With an increase in the composite angle of the rotor blade

the unsteady wake weakens the heat transfer on the suction surface.The unsteady wakes with different widths have obviously greater influence on heat transfer on the pressure face than that on the suction face.With the wake width of 4mm

the heat transfer coefficient on entire surface of the rotor blade at the downstream reached the best.