关键词: 新型翅片式减涡器;翅片单元结构;共转盘腔;总压损失;旋流比

Abstract: In order to reduce the pressure loss during radial air entrainment of compressor, based on the design of the new fins element structure, the effects of new fins element structure on radial air entrainment pressure loss were studied. Numerical study was carried out on the de-swirl system of different rotational speed and new fins structure. The structure of radial air entrainment and pressure loss distribution curve of compressor co-rotating cavity under different working conditions were obtained. The results show that the new fins element structure can restrain the swirl ratio of air flow and reduce the loss of air entrainment pressure, and that the fins element channel width and height have the best value to make the vortex reducer drag reducing effect better. The drag reduction effect is 86.5% higher than that of the simple cavity model under the optimal structure, which the fins element channel width is L=0.78 and the channel height is R₃=0.97. The high and low fins structure can play a better drag reduction effect. With the increase of one side fin height, the drag reduction effect is better when the height increased L₁=0.3, and the drag reduction benefit is the same when the A side or B side fin increases. On the one hand, the drag reduction performance of the optimal high and low fins structure is 87.5%, 29% and 7.8% higher than that of the simple cavity model, the typical fins vortex reducer model and the fins element channel with L=0.78 and R₃=0.97, respectively; on the other hand, the optimal high and low fins structure can reduce the quality of the fins element and has high engineering application value.

Key words: New finned vortex reducer;Finned element structure;Co-rotating cavity;Total pressure loss;Swirl ratio