The harsh environment of thermal and mechanical loads in gas turbine could cause turbine failure. To provide more potential for the blades to handle such harsh environments, thermal barrier coating (TBC) technology is a common solution for such cases. This study focuses on selecting an outstanding high-pressure turbine blade’s material while applying ceramic material of Yttria-stabilized zirconia (YSZ) as coating with an optimized thickness for jet engines. To select the most advantageous alloy, three superior alloys of IN718, IN625, and RENE-41 were considered as blade’s materials to be investigated structurally and thermally through ANSYS©, an engineering simulation software. The results revealed that IN718 outperforms other materials in regards of stress, deformation, and thermal behaviour. Moreover, an optimum thickness of 450 μm showed a compromise between weight cost and maximum performance features.