Effect of tip winglets and blade transition surface modeling on compressor cascade
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摘要:
为了探究不同叶尖小翼与叶片结构过渡曲面造型对压气机叶栅气动性能的影响，在马赫数为0.5时对吸力面叶尖小翼进行变过渡曲面研究，并选取最优过渡曲面方案进行变冲角工况下的流场研究。结果表明：不同过渡曲面造型的叶尖小翼结构都可以改善流场的流动状态，降低流动损失，在设计冲角下，叶尖小翼过渡曲面与叶顶夹角为15°方案的叶尖小翼结构可以使叶栅的总压损失系数降低7.69%。不同冲角下，该叶尖小翼方案对流场都具有改善效果，可以降低流场对冲角变化的敏感性，使叶栅流场状态更加稳定，在6°冲角时，该方案使叶栅的总压损失系数最大降低了9.89%。
Abstract:In order to investigate the effects of different tip winglet structures and cascade transition surfaces on the aerodynamic performance of the compressor cascade, a variable transition surface study was carried out for the suction surface tip winglet under Mach number of 0.5 condition, and the optimal transition surface scheme was selected for the study of the flow field under the variable incidence angle condition. The results showed that the tip winglet structures with different transition surface shapes can improve the flow state of the flow field and reduce the flow loss, and the tip winglet structure with a 15° angle between the transition surface of the tip winglet and the top of the cascade can reduce the total pressure loss of the cascade by 7.69% under the designed incidence angle. Under different incidence angles, the tip winglet scheme had the effect of improving the flow field, reducing the sensitivity of the flow field to the change of incidence angle, and making the flow field of the cascade more stable, and at 6° incidence angle, the scheme reduced the total pressure loss of the cascade by a maximum of 9.89%.
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Key words:
- tip leakage /
- compressor cascade /
- suction side winglet /
- transition surface modeling /
- incidence angle
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图 4 不同网格数目的总压损失系数
Figure 4. Total pressure loss coefficient with different numbers of the grid
图 5 出口截面总压损失系数分布
Figure 5. Total pressure loss coefficient distribution of the outlet section
图 6 不同叶尖小翼方案的叶顶截面静压系数分布
Figure 6. Static pressure coefficient distribution of the tip with different winglet schemes
图 7 不同叶尖小翼方案的出口截面总压损失系数分布
Figure 7. Total pressure loss coefficient distribution of outlet section with different winglet schemes
图 8 不同叶尖小翼方案的叶栅顶部轴向涡量系数分布
Figure 8. Axial vorticity coefficient distribution of tip clearance with different winglet schemes
图 9 不同叶尖小翼方案的节距平均总压损失系数沿叶高分布
Figure 9. Spanwise distribution of pitch-averaged total pressure loss coefficient with different winglet schemes
图 10 不同叶尖小翼方案的总压损失系数数值及相对变化率
Figure 10. Numerical value and relative variation rate of total pressure loss coefficient with different winglet schemes
图 11 不同冲角的叶栅顶部熵分布
Figure 11. Entropy distribution of tip clearance with different incidence angles
图 12 不同冲角的出口截面总压损失系数分布
Figure 12. Total pressure loss coefficients distribution of outlet section with different incidence angles
图 13 不同冲角的叶栅顶部轴向涡量系数分布图
Figure 13. Axial vorticity of tip clearance with different incidence angles
图 14 不同冲角的节距平均总压损失系数沿叶高分布
Figure 14. Spanwise distribution of pitch-averaged total pressure loss coefficient with different incidence angles
图 15 不同冲角的总压损失系数数值及相对变化率
Figure 15. Numerical value and relative variation rate of total pressure loss coefficient with different incidence angles
表 1 叶栅主要参数
Table 1. Main parameters for cascade
参数 数值 弦长b/mm 40 叶片高度h/mm 100 节距t/mm 30 几何进气角/（°） 46.23 安装角/（°） 60 叶顶间隙/mm 3 
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