Akademik Veri Yönetim Sistemi
EUROPEAN CONFERENCES 9th INTERNATIONAL CONFERENCE ON HEALTH, ENGINEERING and APPLIED SCIENCES, Tirane, Arnavutluk, 3 - 05 Nisan 2026, ss.215-225, (Tam Metin Bildiri)
In modern aviation, improving structural efficiency and reducing weight are critical factors for enhancing aircraft performance and sustainability. This study investigates the structural integration of high-bypass-ratio turbofan engines into narrow-body aircraft wings, focusing on the design and optimisation of the engine pylon. A reference configuration based on the CFM56-7B engine is considered, and two widely used aerospace materials, Ti-6Al-4V titanium alloy and 7075-T6 aluminium alloy, are evaluated. The pylon structure is designed using CAD tools and analysed using finite element methods (FEM) in ANSYS and SolidWorks. Static structural analysis, mesh convergence studies, and modal analysis are performed to validate the structural integrity and dynamic behaviour of the system. The results indicate that the titaniumbased design provides superior structural stiffness and safety factor, while the aluminium-based design offers significant weight reduction. Compared to conventional pylon structures, the proposed design achieves up to 53% weight reduction while maintaining compliance with aviation safety standards, including EASA CS-25 and FAA FAR 25. The findings demonstrate that optimised pylon design can significantly enhance aircraft efficiency without compromising safety, providing valuable insights for future aerospace structural design applications
Keywords: Turbofan Engine; Pylon Design; Finite Element Analysis; Structural Optimisation