The inlet distortion problem exists in a boundary layer ingesting propulsion system, and the distortion position is almost stable, which seriously affects the fan performance and stability margin (SM). To effectively improve the distortion resistance of the fan, three non-axisymmetric stator (NAS) schemes are designed according to the parameter distribution law of the distorted flow field in front of the stator under the design conditions in this study, which are based on the solidity matching method of the optimization of the stator inlet geometric angle, chord length, and pitch. The impact of the NAS on the fan performance and the distorted flow field parameters under distorted conditions are numerically studied. The results indicate that NAS can effectively enhance the SM of the fan. Among the three NAS designs, the third one demonstrates a remarkable increase of 74.91% in SM compared to the original fan. The NAS design can promote the fluid re-distribution in the distortion zone, make the aerodynamic parameters more uniform, and thus improve the flow state in the distortion zone. Among the three NAS schemes that are adopted in this research, the NAS design based on the pitch optimization method has the best effect. This design can effectively improve the stator flow field structure, thus significantly improving the SM and the aerodynamic performance of the fan under distortion conditions.

边界层吸气推进系统存在进气畸变问题，畸变位置几乎稳定，严重影响风扇性能和稳定裕度（SM）。为有效提高风机的抗畸变能力，根据本研究设计工况下定子前畸变流场的参数分布规律，设计了三种非轴对称定子（NAS）方案，分别基于定子进气道几何角度、弦长、螺距优化的实体匹配方法。数值研究了变形条件下NAS对风扇性能和变形流场参数的影响。结果表明，NAS可以有效提升风扇的SM。在三款 NAS 设计中，第三款的 SM 相较于原来的风扇有 74.91% 的显着提升。NAS设计可以促进畸变区流体的重新分布，使气动参数更加均匀，从而改善畸变区的流动状态。在本研究采用的三种NAS方案中，基于节距优化方法的NAS设计效果最好。该设计可有效改善定子流场结构，从而显着改善风机在畸变工况下的SM和气动性能。