Influence of trailing edge designs of squealer tips on aerodynamic performance of high-pressure turbine
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摘要:
针对凹槽叶尖，设计全凹槽、压力侧尾切、吸力侧尾切尾缘构型，研究不同尾缘构型及尾切位置对叶尖流动机理及气动性能影响规律。结果表明：压力侧尾切叶尖会导致凹槽涡泄漏位置前移，并且在吸力侧叶尖相应位置附近形成尾切涡，从而导致尾缘下游总压损失增大，最多增加了7.1%；吸力侧尾切叶尖凹槽内流动从切除位置流出而非横跨吸力侧肋边泄漏，总压损失相对减小，最多减小了4.6%。相较于全凹槽叶尖构型和压力侧尾切构型，吸力侧尾切构型具有更优的气动性能。
Abstract:In this article, full cavity squealer tip and several pressure side and suction side cutback blade tips were designed, their detailed flow field and aerodynamic performance were compared with full cavity squealer tip numerically, including vortices inside cavity and flows around blade tip trailing edge, differences in tip leakage flow rate, downstream total pressure loss and entropy rise. The result indicated that pressure side cutback designs caused the cavity vortex leak earlier compared with full cavity tip, a small vortex formed at cut region leading to increase in total pressure loss of 7.1% at most; flow inside cavity left at cut region for suction side cutback designs instead of crossing over cavity wall, downstream total pressure loss was relatively smaller, with the reduction of 4.6% at most. Compared with full cavity and pressure side cutback squealer tip, suction side cutback designs have better aerodynamic performance.
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图 1 高速连续风洞及平面叶栅试验台
Figure 1. High-speed continuous wind tunnel and turbine cascade experimental setup
图 3 五孔探针位置控制设备及安装
Figure 3. Five-hole probe position control equipment and installation
图 5 全凹槽及尾切叶尖模型和几何尺寸
Figure 5. Full cavity and cutback blade tip models and geometries and dimensions
图 6 不同凹槽叶尖构型网格及壁面y+分布
Figure 6. Meshes of different tip geometries and y+ distribution of wall
图 7 全凹槽叶尖构型不同网格密度下叶尖吸力侧展向平均质量通量比
Figure 7. Spanwise averaged mass flux ratio at full cavity blade tip suction side clearance with different grid sizes
图 8 全凹槽叶尖构型叶尖及叶中载荷试验结果与计算结果对比
Figure 8. Comparison of experimental and numerical results of load at full cavity blade tip and midspan
图 9 全凹槽叶尖尾缘下游10%轴向弦长处截面总压损失系数试验结果与计算结果对比
Figure 9. Comparison of experimental and numerical results of total pressure loss coefficient of full cavity blade at 10% axial chord downstream of trailing edge
图 10 全凹槽叶尖构型叶尖流场涡系流线及截面涡量云图
Figure 10. Streamlines of vortices and streamwise vorticity at full cavity blade tip
图 11 不同尾切叶尖构型叶尖流场涡系流线及截面涡量云图
Figure 11. Streamlines of vortices and streamwise vorticity of different cutback blade tips
图 12 压力侧尾切设计叶尖尾缘处主要涡系
Figure 12. Major vortices at blade tip trailing edge of pressure side cutback
图 13 吸力侧尾切设计叶尖尾缘处流场
Figure 13. Flow field at blade tip trailing edge of suction side cutback
图 14 全凹槽与不同尾切设计在尾缘下游10%轴向弦长截面的总压损失系数
Figure 14. Total pressure loss coefficient of full cavity and cutback tips at 10% axial chord downstream of trailing edge
图 15 全凹槽与不同尾切设计在尾缘下游10%轴向弦长截面的平均总压损失系数
Figure 15. Averaged total pressure loss coefficient of full cavity and cutback tips at 10% axial chord downstream of trailing edge
图 16 不同叶尖设计下吸力侧间隙叶尖泄漏量分布云图及展向平均质量通量
Figure 16. Leakage and spanwise averaged mass flux at blade tip suction side clearance of different tip designs
图 17 不同叶尖设计下叶片97%叶高处等熵马赫数
Figure 17. Isentropic Mach number at 97% span of different tip designs
图 18 不同叶尖设计下叶片吸力侧通道截面熵增云图及涡系结构
Figure 18. Entropy rise contours and vortices at suction side passage of different tip designs
图 19 全凹槽与压力侧尾切设计吸力侧通道各截面熵增云图
Figure 19. Entropy rise contours at suction side passage clips of full cavity and pressure side cutback tip
图 20 不同尾缘设计下尾缘下游10%轴向弦长处周向平均总压损失系数沿叶高分布
Figure 20. Circumferentially averaged total pressure loss coefficient distribution along span at 10% axial chord downstream of trailing edge of different blade tip designs
图 21 不同尾缘设计下尾缘下游10%轴向弦长处周向平均气流角沿叶高分布
Figure 21. Circumferentially averaged flow angle distribution at 10% axial chord downstream of trailing edge of different blade tip designs
表 1 试验边界条件
Table 1. Experimental boundary conditions
参数 数值 进口总压 $ {p}_{\mathrm{i}\mathrm{n}}^{*} $/Pa 140 000 进口总温 $ {T}_{\mathrm{i}\mathrm{n}}^{*} $/K 328 出口静压 $ {p}_{\mathrm{i}\mathrm{n}} $/Pa 101 325 出口马赫数 0.65 进口雷诺数（基于叶片轴向弦长） 306 000 进口湍流度/% 5 
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