Comparison of effusion cooling characteristics between different hole configurations in a swirl-stabilized combustor
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摘要:
针对旋流模型燃烧室开展了旋流冲击条件下不同发散冷却孔型（扇形孔和圆孔）传热特性的数值及试验研究。通过稳态液晶测温技术考察了孔型及吹风比对冷却性能的影响。基于稳态数值模拟，完成了不同孔型结构下冷却气流在壁面附近的流动对比分析。试验表明：扇形孔冷效分布特征与圆孔基本相同，但面积平均冷效高出40%左右。相比圆孔，扇形孔流动更易受旋流冲击的影响，导致冷效提高效果对吹风比和位置的改变较为敏感。数值结果表明：扇形孔在角回流区具有更好的气膜覆盖和更多的冷气流量，相比圆孔冷效提高最明显（冷效最高可提高80%左右）；而在冲击区扇形孔冷气流量受到旋流的抑制更明显，冷效的改善不明显。
Abstract:Numerical and experimental studies on the heat transfer characteristics of different effusion cooling hole configurations under swirl impact were carried out in a swirl-stabilized model combustor. The influences of hole configuration and blowing ratio on cooling performance were investigated by steady-state liquid crystal temperature measurement technology. Based on the steady-state numerical simulation, the comparative analysis of the cooling air near the wall was performed for different hole configurations. The experiment results showed that the distribution characteristics of the cooling effectiveness of the fan-shaped hole were basically the same as those of the cylindrical holes, but the average cooling effectiveness of the area was about 40% higher. Compared with the cylindrical holes, the cooling air flow of fan-shaped holes was more susceptible to the impact of swirling flows, such that the improvement of cooling efficiency was more sensitive to the change of blowing ratio and position. The numerical results showed that the fan-shaped hole had better cooling film coverage and more cooling air mass flow in the corner recirculation zone, and the cooling effectiveness was the highest than that of the cylindrical hole (the cooling effectiveness can be increased by about 80% at most). However, the cooling air mass flow of the fan-shaped hole in the impact zone was more obviously inhibited by the swirling flows, and the improvement of cooling effectiveness was not obvious.
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图 6 吹风比与孔型对局部冷效的影响
Figure 6. Influence of blowing ratio and hole structure on local cooling effectiveness
图 7 圆孔与扇形孔冷效沿轴向变化趋势对比（M=3.6）
Figure 7. Comparison of spanwise average efficiency of cylindrical and fan-shaped holes （M=3.6）
图 8 不同区域冷效提高系数对比
Figure 8. Comparison of improvement coefficient of cooling effectiveness at different areas
图 9 吹风比对冷效提高系数的影响
Figure 9. Influence of blowing ratio on improvement coefficient of cooling effectiveness
图 10 燃烧室主流空气流动-基于燃烧室中截面（X/D=0）
Figure 10. Mainstream flow of combustor at the plane （X/D=0）
图 11 近壁面气膜流动对比-基于燃烧室中截面（X/D=0）
Figure 11. Comparison of near-wall coolant film flow at the plane （X/D=0）
表 1 试验工况
Table 1. Experiment and calculation conditions
参数 数值及范围 主流流量/（g/s） 180 冷气流量/（g/s） 5～25 主流温度/K 315 冷气温度/K 300 吹风比 1.2～6.0 
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