Turbine blade research is currently at the forefront of scientific research, owing to its intrinsic connection to materials science and the relatively low efficiency of gas turbines. This study delves into turbine blade enhancement by introducing thermal barrier coatings (TBCs) and environmental barrier coatings (EBCs), utilizing Inconel-713 alloy for the turbine blade. The primary goal of this research is to conduct ANSYS thermal and structural finite element analyses on turbine blades, both with and without the application of TBCs and EBCs, to determine their impact on heat dissipation and structural stability. Various coating materials were employed, including YSZ (Yttria-Stabilized Zirconia), Al2O3, and Si3N4 as TBCs, and BSAS (Barium Strontium Aluminosilicate) as an EBC. The flow behavior over the turbine blades was simulated using ANSYS, and the post-simulation data were compared to assess the effectiveness of the Thermal Barrier Coating and Environmental Barrier Coating. The results showed that utilizing TBC and EBC coatings significantly alters thermal distribution on the blade's surface. Notably, the optimal performance is achieved when using both Si3N4 as the TBC and an EBC which is BSAS in our study.