Film Cooling Adiabatic Effectiveness on a Specific Profile of a Gas Turbine blade that Using Holes with 25 and 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 , Under two different 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 four-hole models increased with increasing the blowing ratio over the whole surface, whereas in the three-row models, relative to the flow direction and surface of the blade, film cooling adiabatic effectiveness have decreased with increasing injection ratio,in the trailing edge region.