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.

阐明压缩机涡流动力学的基本机制对于确定压缩机叶栅中的流量损失来源至关重要。因此，应在微观尺度上分析叶片端部处理对线性压缩机级联的影响。在这项研究中，基于鞍形的拓扑结构和叶片表面上的螺旋点确定了各种叶片端部处理方法的设计参数。然后，基于结果，确定了相应涡旋动力学的潜在机理。结果表明，总流量损失主要由通道和一致的脱落涡旋以及轮廓损失决定。叶片端部处理的积极作用是削弱了涡流结构，它的负面影响是它导致低能流体团聚成分离泡。但是，负面影响可以由正面抵消，从而可以大大减少总流量损失。此外，本研究还分析了处理引起的压力梯度变化。因此，本研究阐明了涡旋结构与流动损失之间的微观关系，并分析了各种叶片端部处理方法对于防止级联流动损失的适用性。