Axial compressors are critical components of gas turbine engines and play a major role in determining overall engine efficiency and combustion performance. Enhancing turbulence at the compressor outlet can significantly improve air–fuel mixing in the combustion chamber. This study investigates a biomimetic surface modification inspired by the natural structure of palm tree leaves applied to the stator blade of the final stage of an axial compressor. The GE-J85 jet engine is selected as the reference configuration and the stator blade profile is based on the NACA 65410 aerofoil.

A palm leaf-inspired riblet pattern is introduced on the stator blade's surface to induce controlled flow disturbances. The pattern is designed with a 45° inclination and a riblet length of 1 mm distributed across the blade surface. The three-dimensional blade geometry is developed using CATIA V5 R20, and numerical analysis is performed using ANSYS under subsonic flow conditions. The aerodynamic and turbulence characteristics of the biomimetic stator blade are compared with those of a conventional smooth stator blade.

The computational results demonstrate a significant enhancement in turbulence parameters for the biomimetic configuration. The turbulent kinetic energy of the modified stator blade increases by approximately 29.5% compared to the baseline design. This increase is indicative of improved flow-mixing capability at the compressor exit. The findings suggest that biomimetic palm leaf surface patterns can be effectively applied to axial compressor stator blades to enhance turbulence and potentially improve combustion efficiency in gas turbine engines. This study highlights the potential of nature-inspired design approaches for advanced aerospace propulsion systems.