| Citation: | SONG Tianchu, WANG Meng, CHEN Xiaohu, et al. Flow control of compressor rotor cascade by blade-attached vortex generator[J]. Journal of Aerospace Power, 2025, 40（7）：20240234 doi: 10.13224/j.cnki.jasp.20240234
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A flow control method in compressor cascade based on blade-attached wedge vortex generator (VG) was proposed, and the numerical simulation of 3D steady Reynolds-averaged Navier-Stokes （RANS） method was carried out. The numerical method was verified, and compared with the experiment results to indicate its correctness. Furthermore, the performance of cascades with four different shape VGs was calculated and the internal flow was analysed. The results showed that the VG with inverted-symmetric shape can effectively improve the cascade performance, and widen the cascade working range. The four-shape schemes can suppress shock wave/boundary layer interaction separation, but the control effects were significantly different. In curved compressor cascade passage, the VG vortex of inverted schemes was close to suction surface, and the control effect was better than that of the forward schemes away from suction surface. The weaker VG vortex pair generated by symmetric scheme can suppress shock wave/boundary layer interaction separation along the axial direction, and the stronger VG vortex from unsymmetric scheme can suppress the separation along the axial and span directions, but with greater static pressure loss. Therefore, considering the separation suppression by VG and its own negative effects, the inverted-symmetric scheme is more suitable for the flow control inside the compressor cascade.
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