The leading edges of aero-engine fan and compressor blades suffer from severe erosion due to the inhalation of suspended particulates in the low-altitude atmosphere during long-term transport. A small deformation of the leading edge can significantly change the aerodynamic performance under a strong non-linear effect, leading to increased operation and maintenance costs for engines. This review first focuses on leading-edge erosion morphology during service, and models of these damages. Secondly, the performance degradation caused by eroded leading edges on different classes of engine components, including airfoils, blades, compression systems, and the whole engine, are reviewed. Finally, optimization methods for eroded blade leading edges and their effects on performance recovery are summarized. This paper contributes to an in-depth understanding of the erosion mechanism of blade leading edges in terms of status and its effect, and is a good reference for establishing erosion leading edge repair methods and improving the level of automated repair.
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.
In order to reduce the fan rotor aerodynamic performance degradation caused by the increasing of blade surface roughness, optimal design of high bypass ratio fan rotor blade with surface roughness was carried out to improve the aerodynamic performance of the fan rotor in long-term flight operation. With the condition of surface roughness uniformly distributed on the blade, the fan blade was optimized by using sweep and lean technology, and the aerodynamic characteristics of the fan blade with different surface roughness were numerically investigated. Numerical results show that the overall aerodynamic performance of the fan rotor decreases as the equivalent sand roughness k s of the blade increasing from 3 μm to 150 μm. The isentropic efficiency of the original blade decreases by 1.56% when the surface roughness reaches 150 μm. Composite sweep and lean optimization was carried out when k s = 80 μm, the isentropic efficiency of the optimized blade at design point is increased by 0.28%, the second optimization based on the optimized blade above by using the reverse lean technology further improved the fan isentropic efficiency by 0.12%, the degradation caused by surface roughness was reduced by optimization, and the robust design of fan rotor blade was achieved.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
customersupport@researchsolutions.com
10624 S. Eastern Ave., Ste. A-614
Henderson, NV 89052, USA
Copyright © 2024 scite LLC. All rights reserved.
Made with 💙 for researchers
Part of the Research Solutions Family.