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The performance of aero engine can be improved effectively by increasing the turbine inlet temperature. For the aerodynamic characteristic of turbine, this paper numerically investigates the aerodynamic characteristic of turbine with different location of air from the film holes in suction side on the turbine blade. The numerical simulations on turbine inner flow field and performance were carried out using the Spalart- Allmaras turbulence model with AGS transition model in low Reynolds number cases. The results show that the boundary layer is increasing. The blade trail surface separate and the aerodynamic characteristic of turbine cascade and stability are also infection. The performance of turbine cascade became worse, and at low Reynolds Number, cooling air can blow boundary layer separating gas in suction side on the turbine blade and have availability effect. The efficiency of the turbine has increasing. The injection locations of 85％ are proven most effective to increase the efficiency of turbine peak value. The most efficiency increase 1.684％.