Stress and Deformation Analysis of Jet Engine Fan Blades under Operational Loads Using FEM

The performance and reliability of jet engine fan blades are critical for aerospace applications, where materials are subjected to high rotational speeds, thermal loads, and mechanical stresses. This study investigates the mechanical behaviour of fan blades constructed from Nickel Alloy, Titanium Alloy, and Ceramic Matrix Composites (CMC) under operational loads using the Finite Element Method (FEM). The analysis incorporates total deformation, von Mises stress, and von Mises strain as key performance indicators. Nickel Alloy demonstrated moderate deformation (0.21428 mm) with stress levels (314.71 MPa) within safe limits, confirming its historical usage in turbine components. Titanium Alloy offered weight reduction but exhibited higher deformation (0.29623 mm) and stress (391.55 MPa), suggesting a trade-off between structural flexibility and mechanical robustness. CMC blades showed superior stiffness with minimal deformation (0.17892 mm) and low stress (199.34 MPa), highlighting their potential for high-efficiency designs; however, their brittle nature poses reliability challenges under impact loads. A comparative analysis emphasizes design trade-offs, demonstrating that while CMC offers the highest efficiency, Nickel and Titanium alloys remain practical due to toughness and fatigue resistance. The study provides insights for material selection, blade geometry optimization, and performance enhancement in modern aero engine applications, offering a foundation for future research on hybrid or coated composite blades to address brittle fracture risks