Thermo-Mechanical Stress Distribution Analysis in Advanced Gas Turbine Blade Materials Using Finite Element Simulation

Abstract

Advanced gas turbine systems operate under extreme thermal and mechanical conditions, making turbine blade reliability a critical factor in enhancing engine efficiency, operational safety, and service life. The increasing demand for high-temperature performance in aerospace and power generation industries has necessitated the development of advanced blade materials capable of withstanding severe thermo-mechanical loading conditions. This research presents a thermo-mechanical stress distribution analysis of advanced gas turbine blade materials using finite element simulation techniques. The proposed study employs finite element analysis (FEA) to investigate the stress, strain, temperature distribution, and deformation characteristics of turbine blade materials subjected to combined thermal and centrifugal loading conditions. The simulation framework incorporates realistic operating parameters, including high rotational speed, elevated combustion temperature, and pressure variations, to evaluate material behavior under practical service environments. Advanced superalloy materials and thermal barrier-coated blade structures are analyzed to identify regions of critical stress concentration and thermal fatigue susceptibility. The numerical model is developed using appropriate meshing techniques and validated through comparative analysis with established engineering standards and existing literature. Performance assessment is conducted based on parameters such as von Mises stress, thermal gradient distribution, deformation rate, and structural stability. The simulation results indicate that advanced nickel-based superalloys with thermal protective coatings exhibit superior resistance to thermo-mechanical stresses and reduced deformation compared with conventional blade materials.