Effect of combustor exit swirl on film cooling characteristics of shaped holes on the pressure surface of high-pressure turbine vanes
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摘要:
为探究燃烧室出口旋流特征对高压涡轮导叶压力面异型孔气膜冷却的影响机理，在定主流进口雷诺数（
Re ）情况下，采用粒子成像测速（PIV）技术结合数值仿真获得了燃烧室出口强旋流流场的分布特征，进而模拟研究了旋流入流对弯扭涡轮导叶流动特性及压力面单排圆柱形孔、扇形孔、前倾孔和簸箕孔气膜冷却特性的影响规律。研究表明：强旋流进气导致压力面产生显著的径向压力梯度，气膜轨迹径向偏转并汇聚至局部区域，带来冷却效率下降、分布不均匀性提高等负面影响。在主流进口Re 不变的情况下，增大吹风比（M ）可有效提升强旋流下各孔型的气膜冷却效率（η ），但仍无法有效改善气膜偏移现象。值得注意的是，强旋流进气并未改变各孔型优劣对比，扇形孔和簸箕孔仍取得了最高的η ；当M =1.2时，扇形孔和簸箕孔相比于圆柱形孔η 最大提升了29.83%和32.29%。Abstract:To elucidate the impact mechanism of swirl characteristics at the combustor exit on the film cooling performance of shaped film cooling holes on the pressure surface of high-pressure turbine vanes, particle image velocimetry (PIV) technology was employed in conjunction with numerical simulations to analyze the distribution characteristics of the strong swirl flow field at the combustor exit under a constant mainstream inlet Reynolds number ($ Re $). Subsequently, numerical simulations were conducted to compare and analyze the effects of swirl inflow on the flow characteristics of the pressure surface of curved and twisted turbine vanes and the film cooling characteristics of single-row cylindrical holes, fan-shaped holes, laid-back holes, and laid-back fan-shaped holes. The results indicated that strong swirl intake induced a significant radial pressure gradient on the pressure surface, causing the film cooling trajectories to radially deflect and converge to localized areas. This led to decreased cooling efficiency and increased non-uniformity of the cooling distribution. When the mainstream inlet $ Re $ remained constant, increasing the blowing ratio (
M ) can effectively enhance the film cooling efficiency (η ) of all hole types under strong swirl conditions, but it cannot effectively mitigate the film offset caused by the swirl. Notably, strong swirl intake did not alter the relative performance ranking of the hole types, but fan-shaped holes and laid-back fan-shaped holes still achieved the highest $ \eta $. WhenM =1.2, the film cooling efficiency of fan-shaped holes and laid-back fan-shaped holes increased by 29.83% and 32.29%, respectively, compared with cylindrical holes. -
图 5 旋流模拟段网格划分及边界条件示意图
Figure 5. Schematic of meshing and boundary conditions for swirling flow simulation section
图 6 叶栅通道段网格划分及边界条件示意图
Figure 6. Schematic of meshing and boundary conditions for cascade passage section
图 10 旋流模拟段出口流动参数分布
Figure 10. Flow parameters distribution on swirl simulation section outlet
图 11 旋流角周向平均值数据对比
Figure 11. Inlet circumferential-averaged swirl angle compared with experimental data
图 12 叶片前缘区域通道截面的极限流线
Figure 12. Limited streamlines of the cascade section on vane leading edge
图 13 压力面极限流线及压力分布
Figure 13. Limited streamlines on the pressure surface and pressure distribution
图 14 不同旋流条件下叶片表面压力系数分布
Figure 14. Surface pressure coefficient distribution under different swirl conditions
图 15 不同吹风比下绝热气膜冷却效率分布云图（$S_{\mathrm{n}} = 0$）
Figure 15. Adiabatic film cooling effectiveness distribution under different blowing ratios （$S_{\mathrm{n}} = 0$）
图 16 不同吹风比下绝热气膜冷却效率面平均值（$S_{\mathrm{n}} = 0$）
Figure 16. Area-averaged adiabatic film cooling effectiveness under different blowing ratios （$S_{\mathrm{n}} = 0$）
图 17 不同吹风比下绝热气膜冷却效率分布云图（$S_{\mathrm{n}} = 0.5$）
Figure 17. Adiabatic film cooling effectiveness distribution under different blowing ratios （$S_{\mathrm{n}} = 0.5$）
图 18 气膜孔出口下游壁面绝热气膜冷却效率及无量纲温度分布（$S_{\mathrm{n}} = 0.5$，$M = 1.2$）
Figure 18. Adiabatic film cooling effectiveness and dimensionless temperature distribution downstream of film cooling holes （$S_{\mathrm{n}} = 0.5$，$M = 1.2$）
图 19 不同吹风比下绝热气膜冷却效率面平均值（$S_{\mathrm{n}} = 0.5$）
Figure 19. Area-averaged adiabatic film cooling effectiveness under different blowing ratios （$S_{\mathrm{n}} = 0.5$）
表 1 导向叶片几何参数
Table 1. Geometric parameters of guide vane
参数 数值 缩放因子 3 叶片弦长$ C $/mm 108 栅距$ P $/mm 81.75 叶高$ H $/mm 56 进口气流角/（°） 90 出口气流角/（°） 34.25 
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表 2 异型孔结构参数
Table 2. Geometry parameters of the shaped holes
参数 前倾孔 扇形孔 簸箕孔 气膜孔直径$D$/mm 1.5 1.5 1.5 孔射流倾角$\alpha $/（°） 45 45 45 展向扩张角$\beta $/（°） 13 13 流向扩张角$\gamma $/（°） 13 13 扩张段占比${L_{\text{e}}}/L$ 7/12 7/12 7/12
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表 3 数值模拟工况
Table 3. Computational conditions
参数 数值 吹风比 0.4, 0.8, 1.2, 1.6 密度比 1.0 旋流强度 0,0.5 主流进口雷诺数/105 1.8
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