Study on the influences of the labyrinth seal structure on the compressor cascade performance
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摘要:
为探究篦齿封严对压气机叶栅性能影响，本文以高负荷压气机平面叶栅为研究对象，设计了5种不同篦齿封严结构，通过数值模拟方法探究5种篦齿封严结构对压气机叶栅性能和流场结构的影响规律。研究结果表明：随着篦齿容腔诱发的泄漏量逐渐增加，叶栅总压损失逐渐增加，叶片载荷能力逐渐减弱。不同篦齿封严结构通过减小间隙泄漏流量，改善叶栅通道内气流的流动状态，进而提高叶片载荷能力，降低通道内的流动损失。5种篦齿方案中，直齿加方块结构对叶栅流场结构和气动性能的改善效果最为显著，其通过阻断齿顶射流，增大齿顶流动阻力，降低篦齿泄漏流量，削弱篦齿泄漏流对吸力面角区分离流动的影响，能够使角区低能流体团缩小32.1%，抑制集中脱落涡影响范围，进而使总压损失降低20%。
Abstract:In order to study the influences of labyrinth seal on compressor cascade performance, the high-load compressor linear cascade was taken as the research object, five different labyrinth seal structures were designed, and the influences of five kinds of labyrinth seal structures on the cascade performance and flow field structure were studied by numerical simulation. The results showed that the total pressure loss of the cascade gradually increased and the blade load capacity gradually decreased as the leakage induced by the labyrinth cavity increased. Various labyrinth seal structures improved the flow condition in the cascade by reducing the clearance leakage flow, thereby improving the blade load capacity and reducing the flow loss. Among the five schemes, the straight tooth with square structure had the most significant improvement effect on the flow field structure and aerodynamic performance of the cascade. By blocking the tip jet, it increased the tip flow resistance, reduced the leakage flow of the labyrinth, and weakened the influence of the leakage flow of the labyrinth on the corner separation flow of the suction surface. It can reduce the volume of low-energy fluid in the corner by 32.1%, inhibit the influence range of the concentrated shedding vortex, and then reduce the total pressure loss by 20%.
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Key words:
- labyrinth seal /
- compressor cascade /
- corner separation /
- aerodynamic performance /
- flow field structure
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图 6 不同方案的总压损失系数和泄漏量
Figure 6. Total pressure loss coefficient and leakage of different schemes
图 7 各方案叶表静压系数曲线
Figure 7. Static pressure coefficient curves of each scheme on the blade surface
图 8 不同方案出口总压损失系数沿叶高分布曲线
Figure 8. Distribution of the total pressure loss coefficient at the outlet along the blade height for different schemes
图 9 不同方案出口气流角沿叶高分布
Figure 9. Distribution of outlet airflow angle along the blade height for different schemes
图 10 不同方案总压损失系数云图
Figure 10. Contour of total pressure loss coefficient of different schemes
图 11 吸力面角区低能流体团及总压损失系数分布
Figure 11. Distribution of low-energy fluid clusters and total pressure loss coefficients in the corner region
图 12 端壁及叶表静压系数云图和极限流线
Figure 12. Static pressure coefficient contours and limiting streamlines on the end wall and blade surfaces
表 1 叶栅几何参数
Table 1. Cascade geometry parameters
参数 数值 弦长 c/mm 60 叶高 H/mm 100 节距 t/mm 33 安装角 γ/（°） 22.15 几何进口角 α/（°） 42 几何出口角 β/（°） 90 进口马赫数 Ma 0.7 
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