Gas turbines are used in jet engines, power plants and other industrial applications. In jet engines, increasing the pressure ratio of the compressor and inlet temperature of the gas turbine are two major methods for increasing the efficiency and output of the motor. In modern gas turbines, in order to increase efficiency, the hot gas temperature usually enters the high pressure turbine at the melting temperature of the alloys used in the manufacturing of the turbine blades. Along with the advances in metallurgy, one of the most common methods for retaining blades and the body of the combustion chamber is using film cooling, in which a layer of cooling flow between the surface and the passing hot gas is formed so that the hot gas output from the combustion chamber that enters the turbine doesn’t damage the blade. The overall purpose of the project is to design a non-uniform Arrangment of elliptical holes for film cooling on a flat plate, that the optimum distance between the rows of holes can optimize the effectiveness of the film cooling. In the film cooling as the layer of the cross section of the cooling hole is more stretched out, due to reduced momentum and better surface coating, the effectiveness increases. For this purpose, two types of cooling holes with elliptic of type II (a/b =2) and type III (a/b =3) have been used in this project. Due to the constant main flow rate, with increasing of blow ratio (M) the velocity of the cooling fluid increases, and as a result, the vertical momentum of the cooling fluid increases. By increasing the blowing ratio to a limit, the coolant fluid separates from the surface and penetrates the mainstream and reduces its effectiveness. Therefore, the centerline and laterally averaged effectiveness diagrams for different blowing ratios were plotted and the highest effectiveness was reported in optimum blow ratio (M = 0.75). In the cooling of the plate by two rows of elliptical holes, as the second row gets closer to the first row of holes, because it covers the distance (width) between the first row of holes, the effectiveness increases. On the other hand, because of the low distance between the first and second rows, the maximum of Von Mises stress is higher than the other configuration. In contrast to the previous configuration, in cooling by three rows of elliptical cross-sectional cooling, by increasing the distance of the second and third row (at an optimum distance) the effectiveness is increased, and the maximum Von Mises stress is reduced. Keywords: Gas turbine, Film cooling, elliptical holes, Blowing ratio, Effectiveness, Von Mises stress