Characteristics of shaped holes on the pressure surface of turbine vane
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摘要:
研究采用数值仿真方法对高压涡轮导叶压力面上圆柱孔、扇形孔、簸箕孔和后置孔的流动和传热特性进行了对比分析。其中扇形孔在展向上扩张12°，后置孔在流向上扩张7°，簸箕孔在两个方向上都有扩张。结果表明：在所研究的吹风比范围内，扇形孔和簸箕孔的气膜冷却效率最大，且当吹风比为2时，扇形孔和簸箕孔的气膜冷却效率分别最高比圆柱孔提高了128.9%和146.9%。此外，簸箕孔的热流密度净收益最大，比圆柱孔提高了28.8%，说明簸箕孔是最佳方案。另外研究发现，展向扩张角对流动和换热特性的影响大于流向扩张角，且气膜冷却效率对热流密度净收益的影响大于传热系数。
Abstract:Numerical simulations were employed to investigate the performance of the flow fields and heat transfer characteristics of four types of film holes: cylindrical holes, fan-shaped holes, laidback fan-shaped holes and laidback holes, on pressure surface of the turbine vane. Fan-shaped holes were expanded with the lateral divergence angle of 12 degrees compared with cylindrical holes, and laidback holes expanded with the forward divergence angle of 7 degrees. Furthermore, laidback fan-shaped holes were expanded in both directions. Results showed that fan-shaped holes and laidback fan-shaped holes showed the maximum film cooling effectiveness within the range of blowing ratios. When the blowing ratio was 2, the film cooling effectiveness of fan-shaped holes and laidback fan-shaped holes was improved to the greatest extent by 128.9% and 146.9%, respectively, in contrast with cylindrical. Additionally, laidback fan-shaped holes had the largest net heat flux reduction, 28.8% higher than cylindrical holes, which indicated the laidback fan-shaped hole was the best scheme. And the forward divergence angle had less influence on the flow and heat transfer characteristics than the lateral divergence angle due to inobvious advantages of laidback holes. Besides, the effect of the film cooling effectiveness on net heat flux reduction was dominant on account of similar distributions of net heat flux reduction and the film cooling effectiveness.
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Key words:
- film cooling /
- heat transfer coefficient /
- shaped holes /
- turbine vanes /
- pressure surface
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图 2 流体域及孔排布位置示意图（单位：mm）
Figure 2. Geometry of the computational domain and hole position （unit： mm）
图 6 气膜冷却效率分布云图
Figure 6. Distribution of the film cooling effectiveness on pressure surface
图 7 展向平均气膜冷却效率沿程曲线图
Figure 7. Spanwise-averaged film cooling effectiveness at dimensionless axial positions
图 8 气膜空下游3个位置的速度分布及流线图（x/D=0, 2.5, 5）
Figure 8. Velocity distribution and streamlines of the three sections of hole（x/D=0, 2.5, 5）
图 9 不同气膜孔的面积平均绝热气膜冷效随吹风比变化曲线图
Figure 9. Area-averaged film cooling effectiveness of different holes with different blowing ratios
图 11 孔出口下游的壁面温度分布及湍动能分布（M=2）
Figure 11. Temperature distribution in flow direction and turbulent kinetic energy distribution of three downstream sections （M=2）
图 12 中间叶高截面湍动能分布及流线图（M=2）
Figure 12. Streamlines and turbulent kinetic energy distribution of X-Y plane at middle vane height （M=2）
图 14 展向平均热流密度净收益曲线图
Figure 14. Spanwise-averaged net heat flux reduction at different dimensionless axial positions
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