| Citation: | SHI Lei, GUO Shuhan, MA Pengyu, et al. Multi-objective optimization remodeling of eroded leading edge of supersonic fan blade[J]. Journal of Aerospace Power, 2025, 40（6）：20220936 doi: 10.13224/j.cnki.jasp.20220936
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To address the performance degradation caused by eroded leading edge of aero-engine supersonic fan blade, a Kriging model between the curvature control point of fan blade leading edge and three optimization objectives of total pressure loss coefficient, total pressure recovery coefficient and material removal rate was constructed, and the second Non-dominated Sorting Genetic Algorithm (NSGA-Ⅱ) was used to optimize the eroded leading edge. The results showed that the material removal rate was negatively correlated with the total pressure loss coefficient, and positively correlated with the total pressure recovery coefficient. Compared with the eroded cascade, the total pressure loss coefficient of the blade with trimmed leading edge decreased by 8.74%, the total pressure recovery coefficient increased by 2.31%, and the material removal rate was 1.94%. Optimized cascade was able to improve the flow around the leading edge, and reduce the intensity of the lip shock and the area of the subsonic region. The bow shock of the eroded cascade intersected the passage normal shock on the suction side, which intensified the interaction with the boundary layer. The optimized cascade made the passage shock move forward, and the shock waves met in advance within the passage, thus restraining the development of the wake.
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