Effect of suction leading edge vortex generator on characteristics of compressor cascade
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摘要:
以压气机平面叶栅实验件为研究对象，在叶栅端壁靠近吸力面前缘布置涡流发生器，来改善压气机静叶气动性能并控制角区分离流动。采用数值模拟的方法，研究不同高度、长度和节距位置的涡流发生器对角区分离流动和气动性能的影响。研究结果表明：吸力面前缘涡流发生器在通道进口端壁附近产生诱导涡，抑制角区低能流体聚集，使分离起始点后移，缩小角区沿着节距方向范围，降低流动损失。涡流发生器应设置在角区分离起始位置，角区分离控制效果随着涡流发生器高度的增高先增强后减弱，随着涡流发生器的弦长增加逐渐减弱，随着布置位置远离吸力面而先增强后减弱，当涡流发生器布置在端壁回流区与主流区交界线、弦长为25%叶片弦长、高度等于2%叶高时，叶栅流动损失减小10.3%。
Abstract:A compressor linear cascade was studied, and vortex generators were arranged near the suction leading edge of the end wall to improve the stator aerodynamic characteristic and control the corner separation. The effects of the vortex generators with different heights, lengths, and pitch positions on the corner separation flow and aerodynamic characteristics were studied by numerical simulation. The results showed that the suction leading edge vortex generator can generate the induced vortex near the end wall of the passage inlet, which inhibited the accumulation of low-energy fluids in the corner region, shifted the separation starting point backward, and narrowed the corner region along the pitch direction, thereby reducing the flow loss. The vortex generator should be arranged at the starting position of the corner separation. The control effect of the corner separation first increased and then decreased with the increase of the height of the vortex generator. With the increase of the chord of the vortex generator, it gradually decreased. As the arrangement position was far away from the suction, it first increased and then decreased. When the vortex generator was arranged at the boundary between the end wall recirculation region and the mainstream region, the chord was equal to 25% of the blade chord, and the height was equal to 2% of the blade height, the flow loss can be reduced by 10.3%.
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图 8 不同高度方案对$ {\overline C _{{\text{pt}}}} $的影响
Figure 8. Effect of different height schemes on $ {\overline C _{{\text{pt}}}} $
图 9 不同高度方案下Cpt 的径向分布
Figure 9. Radial distribution of Cpt values under different height schemes
图 10 不同高度方案下叶根静压系数曲线
Figure 10. Static pressure coefficient curves of leaf roots under different height schemes
图 11 不同高度方案端壁及吸力面极限流线和静压系数
Figure 11. Static pressure coefficient contour and limiting streamlines of the end wall and the suction under different height schemes
图 12 不同高度方案下的三维涡系结构
Figure 12. Three-dimensional vortex structure under different height schemes
图 13 不同弦长方案对$ {\overline C _{{\text{pt}}}} $的影响
Figure 13. Effect of different chord schemes on $ {\overline C _{{\text{pt}}}} $
图 14 不同弦长方案下叶根静压系数曲线
Figure 14. Static pressure coefficient curve of leaf roots under different chord schemes
图 15 不同弦长方案端壁及吸力面极限流线和静压系数
Figure 15. Static pressure coefficient contour and limiting streamlines of the end wall and the suction under different chord schemes
图 16 不同弦长方案下的三维涡系结构
Figure 16. Three-dimensional vortex structure under different chord schemes
图 17 不同位置方案对$ {\overline C _{{\text{pt}}}} $的影响
Figure 17. Effect of different location scheme on $ {\overline C _{{\text{pt}}}} $
图 18 不同位置方案下Cpt径向分布
Figure 18. Radial distribution of Cpt under different location schemes
图 19 原型方案以及方案9的出口总压损失、轴向涡量和二次流
Figure 19. Total pressure loss, axial vortex and secondary flow of the ORI and Case 9 outlet
图 20 不同位置方案下的三维涡系结构
Figure 20. Three-dimensional vortex structure under different position schemes
图 21 改型前后叶栅通道内涡系结构
Figure 21. Vortex structure in the cascade passage before and after modification
表 1 叶栅几何参数
Table 1. Cascade geometry parameters
参数 数值 弦长 c/mm 40 叶高 H/mm 100 节距 t/mm 30 安装角 γ/（°） 60 几何进口角 α/（°） 46.23 几何出口角 β/（°） 76.93 进口马赫数 Ma 0.7 
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表 4 不同位置方案
Table 4. Different location schemes
方案编号 $ \overline {t_{}^{}} $/% 6 5 8 10 9 15 10 20 11 25
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