International Journal of Scientific Research and Engineering Development

The continuous drive to raise turbine entry temperature (TET) in gas turbine engines, in pursuit of higher thermodynamic efficiency, has pushed nickel-based superalloys beyond their inherent thermal capability. High-Temperature Hybrid Composite Coatings, and in particular advanced Thermal Barrier Coatings (TBCs), are therefore indispensable for protecting turbine blades against extreme heat, oxidation, hot corrosion and thermal shock. Conventional YttriaStabilized Zirconia (YSZ) coatings suffer from high-temperature sintering, Calcium-Magnesium-Alumino-Silicate (CMAS) infiltration, and spallation driven by Thermally Grown Oxide (TGO) growth stresses. This paper presents a comparative performance analysis of hybrid composite coating systems, combining a critical literature review with a finite-element-informed thermo-mechanical simulation. Four architectures — conventional YSZ/MCrAlY, a La2Ce2O7 hybrid, a Functionally Graded Coating (FGC), and a High-Entropy Oxide (HEO) hybrid — are modelled under identical thermal boundary conditions representative of a turbine blade aerofoil. Results show that hybrid and graded architectures reduce substrate temperature and, to a lesser extent, interfacial stress relative to the conventional baseline, but that TGO growth stress dominates end-of-life interfacial stress for all architectures, indicating that TGO growth control is at least as important as top-coat chemistry selection for extending coating life.

Dr. Shailendra Kumar Bohidar, Shubham, "Comparative Performance Analysis of High-Temperature Hybrid Composite Coatings for Gas Turbine Blades" International Journal of Scientific Research and Engineering Development, V9(4): Page(1306-1313) July-August 2026. ISSN: 2581-7175. www.ijsred.com. Published by Scientific and Academic Research Publishing.