Film Cooling Adiabatic Effectiveness on a Profile of a Gas Turbine blade that Using Holes with 45 Degree Combined Angles to the Flow Direction and Radial Along the Attack Edge as well as 25 Degree Angles to the Flow Direction and Surface Area of the Attack Edge Area and 35 degrees relative to the outlet hole suefaces along stagnation line, Under a specified blowing ratios, using the Reynolds stress approach and the SST turbulence model, have been investigated by using ANSYS FLUENT commercial software. The results show that the film cooling adiabatic effectiveness in the areas near the blade base is strongly affected by these compond angles, while approaching the upper blade areas, the film cooling effectiveness will not be affected by these injection angles.