Numerical Investigation on Effect of Thermal Barrier Coatings on Gas Turbine Combustor

Abstract—Thermal barrier coatings (TBCs) are critical for enhancing the performance and durability of gas turbine combustors by insulating metal components from extreme combustion temperatures. This project aims to conduct a comprehensive numerical investigation to evaluate the effects of TBCs on the thermal and fluid dynamics within gas turbine combustors. By using computational fluid dynamics (CFD) and heat transfer simulations, the study will analyze how different TBC materials, thicknesses, and configurations impact the overall combustion performance, including temperature distribution, thermal stresses, and efficiency. The study will simulate various operating conditions to investigate the behavior of coated and uncoated turbine surfaces. Key objectives include determining the reduction in surface temperatures of turbine blades, evaluating thermal gradient control, and assessing the influence of TBCs on component life and fuel efficiency. The results provide insights into optimizing TBC applications to enhance gas turbine performance and durability. The obtained results provided insights into the optimal application of TBCs and various materials as TBC, highlighting their potential to extend component lifespan and enhance gas turbine efficiency. This investigation will contribute to the ongoing efforts in improving gas turbine technology, with implications for aerospace and power generation sectors, ultimately leading to more sustainable and efficient energy solutions. Keywords—Thermal Barrier Coatings, Gas Turbine Combustor, Computational Fluid Dynamics, Heat Transfer, Thermal Management, Combustor Efficiency.