Abstract: In order to investigate the effect of swirl distortion on the performance and stability of compressor， a method for designing blade type swirl distortion screen was presented. Four particular types of swirl distortion were produced by placing turning vanes and structural supports in a pattern which directly matches the desired swirl vector field. The swirl flow produced by the swirl distortion screen was analyzed using Computational Fluid Dynamics(CFD) techniques with detailed comparison with target swirl flow fields. The numerical simulation results show that the swirl distortion screen can produce both desired intensity of bulk swirl and twin swirl at the exact location. The swirl distortion screen can also be used to match swirl profiles obtained from a particular S-shaped duct or a hybrid wing body aircraft. The deviations of average swirl angles on three measurement rings of Aerodynamic Interface Plane(AIP) between profiles produced by swirl distortion screen and their corresponding desired swirl profiles are 0.19°， 0.64°， 1.56°， 2.48° respectively， which demonstrate that the swirl distortion screen is able to reproduce the target swirl profile accurately to achieve the design requirement.

Key words: Swirl distortion；Distortion screen；S-shaped duct；Hybrid wing body

摘要： 为进一步研究旋流畸变对压气机性能和稳定性的影响，提出了一种叶片式旋流畸变网的设计方法，根据目标旋流场设置旋流畸变网的转向叶片和支撑结构，产生了4种特定流场结构和强度的旋流畸变。利用CFD技术对畸变网产生的旋流场与目标旋流场进行了详细对比研究。结果表明，旋流畸变网能够在指定的位置产生期望强度的整体涡和对涡旋流，并且能够准确复现出由S弯进气道和翼身融合体飞机形成的复杂结构形式的旋流畸变场；在气动交界面的3个测环上，畸变网产生的旋流场与4类目标旋流场的旋流角平均偏差分别为0.19°，0.64°，1.56°，2.48°，表明旋流畸变网对目标旋流场的复现有效性较强，满足了畸变网的设计需求。

关键词: 旋流畸变；畸变网；S弯进气道；翼身融合体