In order to increase turbine efficiency and prevent metal materials from being corroded by high temperatures, one of the great important methods for turbine blade cooling is film cooling. This work explores numerically the effects of various curvature wall on film cooling performance, and the effects of three different hole structures and four various blowing ratios (0.25,0.5,1,1.5) were discussed. Results show that the film cooling effectiveness values of the various configurations (cylindrical hole, shaped-hole, trenched shaped-hole) on the convex wall are 112%, 76%, and 50% higher than that on the concave wall respectively when the blowing ratio is 0.25, which indicates convex wall exhibits a greater potential to release the cooling effects of the jet holes compared with the concave wall and flat wall. Moreover, trenched shaped-holes provide a more uniform protection for wall, especially in terms of the coverage area in the spanwise direction. At the ends of the xs/D = 5 line, the cooling performance of trenched shaped-holes are locally 1320% and 1610% higher than cylindrical holes and shaped-holes, respectively. Additionally, when the blowing ratio is high, compared to curved walls, trenched shaped-holes have the most significant effect on improving the film cooling of flat wall surfaces.