Aerodynamic Performance of a Multi-stage Axial Compressor with Tip Clearance Coupled with Hub Fillet

Turbo jet is one of the most important components of jet plane. Improving the performances of the engine has always been a prime concern of engineers. It is clearly essential to identify the structure and aerodynamic characteristics of engine to maximize the performances of it. This paper presents an investigation of tip clearance and fillet radius parameter on aerodynamic performances of a multi-stage axial compressor using three-dimensional (3-D) Reynolds-averaged Navier-Stokes equations with the k-ω SST model. A numerical validation was tested to. Two geometric parameters of a multi-stage axial compressor with tip clearance for only rotor blades and fillet radius for both of rotor and stator blades were investigated in this research to demonstrate the effect on total pressure ratio, adiabatic efficiency, stall margin. The numerical results showed that the adiabatic efficiency increases with a decrease of tip clearance, whereas radius fillet doesn’t affect the aerodynamic characteristic. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.