Thermal and Structural Performance Analysis of YSZ-Coated Titanium Gas Turbine Blades Using ANSYS

Abstract

Gas turbine blades operate under severe thermal and mechanical environments, making their durability and efficiency essential for reliable aerospace and power generation applications. This study investigates the design and numerical evaluation of yttria-stabilized zirconia (YSZ) thermal barrier coatings applied on titanium alloy gas turbine blades using computer-aided design and finite element analysis. Initially, a three-dimensional turbine blade model was developed in SolidWorks, followed by structural and thermal performance assessments in ANSYS. The behavior of both coated and uncoated blade configurations was examined under applied mechanical loading and high-temperature operating conditions. Key performance parameters, including deformation, equivalent stress, elastic strain, temperature distribution, total heat flux, and directional heat flux, were analyzed to determine the influence of the YSZ coating. The simulation results demonstrated that the application of the YSZ coating improved the thermal protection capability and enhanced the overall performance of the turbine blade. The coated blade exhibited reduced thermal exposure and improved resistance against heat transfer compared with the uncoated configuration. Furthermore, the coating contributed to better stress distribution and structural stability under operating conditions. The findings confirm the potential of YSZ thermal barrier coatings as an effective approach for improving the service life, reliability, and efficiency of gas turbine components. This research provides valuable insights into simulation-based coating optimization and supports the development of advanced turbine blade technologies for high-temperature applications.