Abstract
Elucidating the underlying mechanism of the vortex dynamics in compressors is essential for determining the sources of the flow losses in compressor cascades. Hence, the effects of blade-end treatments on a linear compressor cascade should be analyzed at the microscale. In this study, the design parameters for various blade-end treatment methods were determined based on the topological structure of the saddle and spiral points on the blade surface. Then, based on the results, the underlying mechanism of the corresponding vortex dynamics was determined. The results showed that the total flow loss is primarily determined by the passage and concerted shedding vortices and the profile losses. The positive effect of the blade-end treatment is that it weakens the vortex structures, while its negative effect is that it causes the low-energy fluid clusters to converge into a separation bubble. However, the negative effects are compensated for by the positive, resulting in a significant reduction in the total flow loss. Furthermore, the changes induced in the pressure gradients by the treatments were also analyzed in this study. Thus, the microscale relationship between the vortex structure and the flow loss was clarified and the suitability of various blade-end treatment for preventing cascaded flow losses was analyzed in this study.
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