THERMAL AND STRUCTURAL ANALYSIS OF T6, HAYNES 188 AND X-40 GAS TURBINE BLADE AT VARIOUS OPERATING TEMPERATURES
DOI:
https://doi.org/10.11113/aej.v16.25087Keywords:
Gas Turbine Blades, Finite Element Analysis, Solidworks, ANSYS., Gas Turbine Blades, Finite Element Analysis, Ti-T6, Haynes 188, X-40, Cooling Holes, ANSYS.Abstract
Gas turbine blades operate under extreme thermal and mechanical loads, requiring efficient cooling strategies and materials with high-temperature resistance. This study presents a comparative thermal and structural analysis of blades made from Ti-T6, Haynes 188, and X-40 using finite element analysis (FEA). Blade models with 8, 12, and 16 radial cooling holes were developed in SolidWorks and analysed in ANSYS 2023 R1 under steady-state conditions from 800 °C to 1600 °C. Thermal performance was evaluated through temperature distribution, while structural behavior was assessed using deformation, strain, and stress. Results showed that additional cooling holes reduced blade temperature, with Ti-T6providing the best thermal performance but exhibiting higher deformation and strain due to its lower stiffness. Haynes 188 and X-40 demonstrated greater structural stability, with X-40 maintaining the most uniform stress distribution. Overall, X-40 offers the best balance between cooling efficiency and structural integrity, making it a promising choice for advanced turbine blade applications.
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