Influence Of Fan Rotor Leading Edge Erosion On The Flow Characteristics Of The Compression System

Abstract

During the operation of an aero-engine, the leading edge of the fan rotor blade is eroded by airflow, resulting in changes in the blade leading edge morphology, which in turn affects the overall aerodynamic level of the compression system. Based on the study of the degradation of fan rotor aerodynamic characteristics by leading edge erosion, the study was extended to the whole compression system. This paper uses numerical simulation to calculate the flow characteristics of the compression system for the original blade and fan rotor leading edge roughness Rs=120μm, and analyzes the aerodynamic performance at the design speed. In the bypass duct near the stall point, The isentropic efficiency of the eroded blade is 2.082% lower compared to that of the original blade, and the pressure ratio is 0.34% lower compared to that of the original blade, but the leading edge erosion of the fan blade has relatively little effect on the core duct.