Numerical study on discrete film cooling performance of non-axisymmetric endwall
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摘要:
非轴对称端壁可有效实现对叶栅内部周向压差及复杂二次流的调控，从而改善叶栅气动性能，同时端壁造型会对气膜孔出口面积和冷气轨迹产生显著影响。研究通道表面分别沿周向与流向发生凹凸变化，探究不同造型位置对气膜孔冷却特性的影响规律，在非轴对称叶栅通道内部10%
C ax、40%C ax与70%C ax位置处分别设置气膜孔排，研究叶栅内部端壁造型对气膜孔冷却特性的影响规律。研究表明：仅考虑周向凹凸变化时，除最凹点与最凸点外，其余位置均可有效改善大吹风比下冷气的吹离现象。仅考虑流向发生凹或凸变化时，在最凹点之后，最凸点之前，孔出口面积明显增大，相较于平板气膜孔的出口面积最大可增加51.4%，高冷效区域也显著增大。在叶栅通道中采用压差法得到的非轴对称端壁可降低叶栅内部周向压差，减弱马蹄涡压力面侧分支强度，改善其气动性能，位于非轴对称叶栅通道内部的气膜孔排，端壁造型可提升冷气贴壁性，在大吹风比下，整体冷却性能更优，M =1.0和M =1.5时，η >0.2的高效冷却面积占比相较于原型端壁分别提高5.58%、5.51%。Abstract:The non-axisymmetric endwall can effectively reduce the circumferential pressure difference and control the complex secondary flow inside the passage. Consequently, this enhanced the aerodynamic performance of the airfoil. The non-axisymmetric endwall significantly impacted the outlet area of the film holes and the trajectory of the coolant. The concave-convex changes along the circumferential and axial directions on a flat plate were studied to explore the effects of different shaping positions on the film cooling characteristics. A row of discrete film holes at positions of 10%
C ax, 40%C ax, and 70%C ax inside the non-axisymmetric vane cascade were positioned. The numerical method of solving the time-averaged Reynolds equations was used to investigate the influence of the endwall shape on the cooling characteristics of the film holes. The results were as follows. Only when there were concave-convex changes along the circumferential direction on the flat plate, excluding the most concave and convex points, could other positions effectively reduce the blow-off of the coolant jet at a high blowing ratio. In the case of concave or convex changes along the axial direction, the exit area of the holes significantly increased behind the most concave point and in front of the most convex point. Compared with the flat plate, the maximum outlet area of the holes can increase by 51.4%, resulting in a substantial expansion of the high adiabatic effectiveness region. The non-axisymmetric endwall profiling based on passage pressure difference method can reduce the circumferential pressure gradient and the intensity of the horse-shoe vortex, improving aerodynamic performance. The endwall shaping in the film hole arrangement can improve the coolant attachment. The overall cooling performance was better under a higher blowing ratio. WhenM =1.0 andM =1.5, the area of high adiabatic effectiveness region withη >0.2 can be increased by 5.58% and 5.51%, respectively, compared with the flat endwall. -
图 6 方通道表面周向凹凸变化结构及孔出口形貌图
Figure 6. Circumferential contouring of rectangular channel and the shape of film cooling hole outlet
图 7 具有不同周向曲率的气膜孔随吹风比的增大气膜冷却效率分布
Figure 7. Distribution of film cooling efficiency for film holes with different circumferential curvatures as the blowing ratio increasing
图 8 具有不同周向曲率的气膜孔中心面位置无量纲温度及速度矢量分布（M=0.5）
Figure 8. Non-dimensional temperature and vector distribution at the center plane of a hole with different circumferential curvatures （M=0.5）
图 9 具有不同周向曲率的气膜孔出口面积增量及高效冷却（η>0.15）面积增量
Figure 9. Increased area of the hole with different circumferential curvatures and high effective coolant coverage area（η>0.15） at different positions
图 10 通道表面流向凸变化结构及孔出口形貌图
Figure 10. Position and shape of film cooling hole on the convex wall
图 11 通道表面流向凸变化不同位置的气膜孔随吹风比增大气膜冷却效率分布
Figure 11. Distribution of film cooling efficiency for holes at different positions on the convex wall as the blowing ratio increases
图 12 通道表面流向凸变化不同位置的气膜孔中心面位置无量纲温度及速度矢量分布（M=0.5）
Figure 12. Non-dimensional temperature and vector distribution at the center plane of a hole at different positions on the convex wall （M=0.5）
图 13 通道表面流向凸变化不同位置的气膜孔出口面积增量及高效冷却（η>0.15）面积增量
Figure 13. Increase area of the hole outlet and effective coolant coverage area （η>0.15） at different positions on the convex wall
图 15 通道表面流向凹变化不同位置的气膜孔随吹风比增大气膜冷却效率分布
Figure 15. Distribution of film cooling efficiency for holes at different positions on the concave wall as the blowing ratio increasing
图 16 通道表面流向凹变化不同位置的气膜孔中心面位置无量纲温度及速度矢量分布（M=0.5）
Figure 16. Non-dimensional temperature and vector distribution at the center plane of a hole at different positions on the concave wall （M=0.5）
图 17 通道表面流向凸变化不同位置的气膜孔出口面积增量及高效冷却（η>0.15）面积增量
Figure 17. Increase area of the hole outlet and effective coolant coverage area （η>0.15） at different positions on the concave wall
图 22 端壁表面气膜冷却效率分布
Figure 22. Distribution of film cooling effectiveness on the endwall
图 23 端壁表面周向平均气膜冷却效率沿轴向的分布
Figure 23. Laterally averaged film effectiveness distribution on the endwall
图 24 12%Cax、42%Cax和72%Cax 位置处无量纲温度分布
Figure 24. Distribution of film cooling effectiveness at 12%Cax，42%Cax and 72%Cax sections
表 1 几何参数
Table 1. Geometric parameters
参数 数值 C/mm 594 Cax/mm 293 P/C 0.77 H/C 0.93 d/mm 4.6 进口气流角/（°） 0 出口气流角/（°） 72 
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表 2 计算边界条件
Table 2. Computational boundary conditions
参数 数值 主流温度/K 333.19 主流进口总压/kPa 107.64 冷气进口总温/K 293.15 进口湍流度/% 1 出口静压/kPa 107 质量流量比/% 0.6
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表 3 端壁表面高冷却效率（η>0.2）面积占总面积比例
Table 3. Proportion of high cooling efficiency （η>0.2） area on the end wall surface to the total area
% 结构 M=0.5 M=1.0 M=1.5 原型端壁 28.48 36.52 19.28 非轴对称造型端壁 27.14 42.10 24.78
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