Analysis on film cooling hole arrangement effect for rotating blade leading edge
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摘要:
研究了旋转动叶前缘两侧区域双排孔的孔排布局对气膜冷却特性的影响。采用数值模拟方法获得前缘气膜冷却效率分布以及流动特性。在前缘滞止线每一侧布置两排气膜孔，第1排气膜孔与滞止线夹角为±10°，通过调整第2排孔的径向位置和流向位置实现不同的单侧双排孔布局。结果表明：在前缘两侧区域，双排气膜孔布局对气膜冷却特性的影响规律并不相同。在前缘偏吸力面侧区域，孔排布局对相邻孔排的射流掺混特征具有显著影响；而在前缘偏压力面侧区域，双排孔密布的布局形式可以获得更好的气膜冷却效果，这种效应在近孔区域更加明显。吸力面和压力面侧最佳布局的冷却效率提升分别为0.07和0.02。
Abstract:The effects of hole arrangement of two rows of film holes on the film cooling performance at each side of rotating blade leading edge were investigated. The film cooling performance and flow filed were obtained by using numerical simulation method. The first row of film holes was fixed at ±10° downstream stagnation line and was followed by the second row of holes. The span-wise position and the stream-wise location of the second row of holes were adjusted to achieve different hole arrangement. The results indicated that the effects of hole arrangement of two rows on film cooling were different at two sides of the leading edge. At the leading edge suction side, the relative position between two rows of holes significantly affected the interaction between the adjacent jets from two rows. At the pressure side, closer distance between two adjacent holes in two rows produced better film cooling performance. Meanwhile, the effect of relative position between two rows of holes was mainly located in the near hole region. The film cooling effectiveness at the suction side and pressure side increased by 0.07 and 0.02, respectively.
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Key words:
- leading edge /
- film cooling effectiveness /
- rotating blade /
- hole arrangement /
- turbine
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图 2 前缘和吸力面侧气膜孔排布示意图
Figure 2. Schematic views of leading edge and hole arrangement in suction side
图 6 前缘吸力面侧不同孔排展向距离下气膜冷却效率分布云图
Figure 6. Contours of film cooling effectiveness at various spanwise hole arrangements in suction side of leading edge
图 7 不同孔排布局下流向位置s/d= −3.5处涡量分布
Figure 7. Streamwise-vorticity distributions on plane s/d= −3.5 with varied spanwise hole arrangement
图 8 不同孔排流向距离下前缘吸力面侧气膜冷却效率分布云图
Figure 8. Contours of film cooling effectiveness at various streamwise hole arrangements in suction side of leading edge
图 9 前缘吸力面侧面积平均气膜冷却效率
Figure 9. Area-averaged film cooling effectiveness in suction side of leading edge
图 10 前缘压力面侧不同孔排展向距离下气膜冷却效率分布云图
Figure 10. Contours of film cooling effectiveness at various spanwise hole arrangements in pressure side of leading edge
图 11 不同孔排布局下流向位置s/d=3.5和7截面处无量纲温度分布
Figure 11. Non-dimensional temperature distributions on plane s/d=3.5 and 7 with varied spanwise hole arrangement
图 12 不同孔排流向距离下前缘压力面侧气膜冷却效率分布云图
Figure 12. Contours of film cooling effectiveness at various streamwise hole arrangements in pressure side of leading edge
图 13 前缘压力面侧面积平均气膜冷却效率
Figure 13. Area-averaged film cooling effectiveness in pressure side of leading edge
表 1 前缘结构参数
Table 1. Configuration dimensions of leading edge
参数 数值 孔径d/mm 0.8 前缘直径D/d 10 前缘壁厚δ/d 2.5 第1排孔流向位置α1/（°） ±10 第2排孔流向位置α2/（°） ±25, ±40 展向倾角β/（°） 30 流向倾角γ/（°） 90 单排孔间距P1/d 7.875 两排孔相对径向间距P2/P1 1/4, 2/4, 3/4 叶片高度H/mm 80 
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表 2 计算工况
Table 2. Detailed computation conditions
参数 数值 主流雷诺数Reg 0.8 导叶入口湍流度Tu/% 5 动叶进口相对速度Vrel/（m/s） 10.8 转速Ω/（r/min） ±10 主流温度Tg/K 460 冷气温度Tc/K 300 密度比Rd 1.52 吹风比M 0.5, 1.0, 2.0
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