| Citation: | ZHONG Jingjun, JIA Xinyu, WU Wanyang. Effect of tip winglets and blade transition surface modeling on compressor cascade[J]. Journal of Aerospace Power, 2026, 41（2）：20240389 doi: 10.13224/j.cnki.jasp.20240389
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In order to investigate the effects of different tip winglet structures and cascade transition surfaces on the aerodynamic performance of the compressor cascade, a variable transition surface study was carried out for the suction surface tip winglet under Mach number of 0.5 condition, and the optimal transition surface scheme was selected for the study of the flow field under the variable incidence angle condition. The results showed that the tip winglet structures with different transition surface shapes can improve the flow state of the flow field and reduce the flow loss, and the tip winglet structure with a 15° angle between the transition surface of the tip winglet and the top of the cascade can reduce the total pressure loss of the cascade by 7.69% under the designed incidence angle. Under different incidence angles, the tip winglet scheme had the effect of improving the flow field, reducing the sensitivity of the flow field to the change of incidence angle, and making the flow field of the cascade more stable, and at 6° incidence angle, the scheme reduced the total pressure loss of the cascade by a maximum of 9.89%.
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