Effect of non-uniform crossflow in coolant channel on film cooling characteristics
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摘要:
为探讨实际涡轮叶片内横流对气膜冷却特性的影响，基于自主开发GCFD代码模拟冷气横流从有限通道一侧到另一侧参数非均匀变化导致的气膜冷却特性改变。研究对象为15孔圆柱型气膜冷却平板，其冷却通道垂直于主流通道、通流面积与气膜孔出流总截面积相等。结果表明：非均匀进气横流与下游堵塞对各气膜孔入口施加切向动量比例不同，使其流动结构发生变化；孔间相互作用进一步导致气膜覆盖呈现冷气迎风侧偏移、背风侧偏移以及维持对称分布等特征。随吹风比从0.2上升到1.5，参数的非线性变化加强，最大流量系数与最小流量系数之比越来越小，最小值为1.04；最大面平均冷效与最小面平均冷效之比越来越大，最大值为3.06。
Abstract:To investigate the effect of crossflow within turbine blades on film cooling characteristics, a numerical study was conducted. An in-house GCFD code was employed to simulate the impact of the non-uniform variation in coolant flow across a limited channel on film cooling characteristics. The research focused on a 15-hole cylindrical film cooling flat plate, where the coolant flow channel is perpendicular to the mainstream flow channel in space. The coolant flow area equals the total cross-sectional area of all film cooling holes. Results show that the non-uniform crossflow and downstream blockage apply different tangential momentum proportions to the entrance of each film hole, causing changes in the flow structure of the holes. The interaction between holes further leads to different characteristics of film coverage, including windward and leeward deviations, as well as a symmetric distribution. As the blowing ratio increases from 0.2 to 1.5, the non-linear variation of parameters intensifies. The ratio of the maximum to minimum discharge coefficient decreases, reaching a minimum value of 1.04. The ratio of the maximum to minimum space-averaged cooling effectiveness increases, with a maximum value of 3.06.
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Key words:
- non-uniform crossflow /
- film cooling /
- cylindrical hole /
- discharge coefficient /
- blowing ratio
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图 2 有限体积法通量计算示意图
Figure 2. Schematic diagram of flux calculation in the finite volume method
图 3 无/有横流进气条件下边界条件设置
Figure 3. Boundary conditions under non-crossflow and crossflow inlet conditions
图 5 单孔气膜冷却平板网格划分
Figure 5. Mesh generation of the flat plate with single-hole film cooling
图 7 无/有横流进气条件下单孔平板气膜冷效分布云图
Figure 7. Contours of film cooling effectiveness on a single-hole plate under non-crossflow and crossflow inlet conditions
图 8 无/有横流进气条件下气膜孔入口截面归一化马赫数云图及流线分布
Figure 8. Normalized Mach number contours and streamlines at hole entrance sections under non-crossflow and crossflow inlet conditions
图 9 吹风比M=0.5工况冷却通道z截面归一化马赫数
Figure 9. Normalized Mach number across the coolant passage at the z cross-section at a blowing ratio of M=0.5
图 10 无/有横流进气条件下多孔平板气膜冷效分布云图
Figure 10. Contours of film cooling effectiveness on a multi-hole plate under non-crossflow and crossflow inlet conditions
图 11 无/有横流进气条件下气膜孔入口截面流线分布
Figure 11. Streamlines at the entrance sections of film holes under non-crossflow and crossflow inlet conditions
图 12 不同吹风比下1～15号气膜孔归一化流量系数
Figure 12. Normalized discharge coefficients of film cooling holes 1—15 at different blowing ratios
图 13 不同吹风比下1～15号气膜孔出口归一化面平均冷却效率
Figure 13. Normalized area-averaged cooling effectiveness at the exits of film cooling holes 1—15 under various blowing ratios
表 1 气膜冷却平板边界条件
Table 1. Boundary conditions for film cooling flat plate
参数 数值 主流通道入口总温Tm0/K 540 冷却通道入口总温Tc0/K 310 主流马赫数Mam 0.3 主流湍流度Tum/% 5.2 吹风比M 0.2, 0.5, 1.0, 1.5 密度比D 1.75 主流雷诺数Rem 32000 
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[1] Kissel H P, Weigand B, von Wolfersdorf J, et al. An experimental and numerical investigation of the effect of cooling channel crossflow on film cooling performance[C]//Proceedings of the ASME Turbo Expo: Power for Land, Sea, and Air. Montreal, Canada: ASME, 2007: 147-158. [2] Schroeder R P, Thole K A. Thermal field measurements for a shaped hole at low and high freestream turbulence intensity[J]. Journal of Turbomachinery, 2017, 139(2): 021012. doi: 10.1115/1.4034798 [3] 王玮琪, 单勇, 廖华琳, 等. 主流压力梯度对气膜冷却效率影响的数值研究[J]. 航空动力学报, 2017, 32(8): 1876-1885. Wang Weiqi, Shan Yong, Liao Hualin, et al. Numerical research on film cooling effectiveness with different mainstream pressure gradient[J]. Journal of Aerospace Power, 2017, 32(8): 1876-1885. (in Chinese doi: 10.13224/j.cnki.jasp.2017.08.012Wang Weiqi, Shan Yong, Liao Hualin, et al. Numerical research on film cooling effectiveness with different mainstream pressure gradient[J]. Journal of Aerospace Power, 2017, 32(8): 1876-1885. (in Chinese) doi: 10.13224/j.cnki.jasp.2017.08.012 [4] 王晓增, 阚瑞, 任明, 等. 高速条件下吸力面复合角孔气膜冷却特性[J]. 航空动力学报, 2023, 38(2): 269-278. Wang Xiaozeng, Kan Rui, Ren Ming, et al. Film cooling characteristics of compound angle hole on suction side under high-speed conditions[J]. Journal of Aerospace Power, 2023, 38(2): 269-278. (in Chinese doi: 10.13224/j.cnki.jasp.20220544Wang Xiaozeng, Kan Rui, Ren Ming, et al. Film cooling characteristics of compound angle hole on suction side under high-speed conditions[J]. Journal of Aerospace Power, 2023, 38(2): 269-278. (in Chinese) doi: 10.13224/j.cnki.jasp.20220544 [5] Cao Nan, Li Xue, Wu Zeyu, et al. Effect of film hole geometry and blowing ratio on film cooling performance[J]. Applied Thermal Engineering, 2020, 165: 114578. doi: 10.1016/j.applthermaleng.2019.114578 [6] 谢婕, 张靖周, 谭晓茗, 等. 气膜孔内部对流换热的数值研究[J]. 航空动力学报, 2010, 25(11): 2507-2513. Xie Jie, Zhang Jingzhou, Tan Xiaoming, et al. Numerical simulation of convective heat transfer inside film cooling hole[J]. Journal of Aerospace Power, 2010, 25(11): 2507-2513. (in Chinese doi: 10.13224/j.cnki.jasp.2010.11.016Xie Jie, Zhang Jingzhou, Tan Xiaoming, et al. Numerical simulation of convective heat transfer inside film cooling hole[J]. Journal of Aerospace Power, 2010, 25(11): 2507-2513. (in Chinese) doi: 10.13224/j.cnki.jasp.2010.11.016 [7] Jiang Y, Capone L, Ireland P, et al. A detailed study of the interaction between two rows of cooling holes[J]. Journal of Turbomachinery, 2018, 140(4): 041008. doi: 10.1115/1.4038833 [8] Mcclintic J W, Fox D W, Jones F B, et al. Flow physics of diffused-exit film cooling holes fed by internal crossflow[J]. Journal of Turbomachinery, 2019, 141(3): 031010. doi: 10.1115/1.4042166 [9] Gritsch M, Schulz A, Wittig S. Effect of internal coolant crossflow on the effectiveness of shaped film-cooling holes[J]. Journal of Turbomachinery, 2003, 125(3): 547-554. doi: 10.1115/1.1580523 [10] Veley E M, Thole K A, Bogard D G. The effects of channel supplies on overall film-cooling effectiveness[J]. Journal of Turbomachinery, 2024, 146(3): 031006. doi: 10.1115/1.4063927 [11] 徐光耀, 于志强, 安柏涛. 垂直横流通道内槽型截面孔气膜冷却特性数值研究[J]. 推进技术, 2020, 41(10): 2248-2259. Xu Guangyao, Yu Zhiqiang, An Baitao. Numerical investigation on film cooling characteristics of slot-sectional holes in perpendicular cross-flow channels[J]. Journal of Propulsion Technology, 2020, 41(10): 2248-2259. (in Chinese doi: 10.13675/j.cnki.tjjs.190576Xu Guangyao, Yu Zhiqiang, An Baitao. Numerical investigation on film cooling characteristics of slot-sectional holes in perpendicular cross-flow channels[J]. Journal of Propulsion Technology, 2020, 41(10): 2248-2259. (in Chinese) doi: 10.13675/j.cnki.tjjs.190576 [12] Thole K A, Gritsch M, Schulz A, et al. Effect of a crossflow at the entrance to a film-cooling hole[J]. Journal of Fluids Engineering, 1997, 119(3): 533-540. doi: 10.1115/1.2819277 [13] McClintic J W, Anderson J B, Bogard D G, et al. Effect of internal crossflow velocity on film cooling effectiveness: Part Ⅰ axial shaped holes[J]. Journal of Turbomachinery, 2018, 140: 011003. doi: 10.1115/1.4037997 [14] Straub D, Weber J, Roy A, et al. Effects of downstream vortex generators on film cooling a flat plate fed by crossflow[J]. Journal of Turbomachinery, 2024, 146(5): 051011. doi: 10.1115/1.4064316 [15] 白江涛, 朱惠人, 刘存良. 内通道交错横流对气膜冷却效率的影响[J]. 航空动力学报, 2008, 23(8): 1353-1358. Bai Jiangtao, Zhu Huiren, Liu Cunliang. Numerical study of the effect of internal coolant crossflow on film cooling effectiveness[J]. Journal of Aerospace Power, 2008, 23(8): 1353-1358. (in Chinese doi: 10.13224/j.cnki.jasp.2008.08.026Bai Jiangtao, Zhu Huiren, Liu Cunliang. Numerical study of the effect of internal coolant crossflow on film cooling effectiveness[J]. Journal of Aerospace Power, 2008, 23(8): 1353-1358. (in Chinese) doi: 10.13224/j.cnki.jasp.2008.08.026 [16] 贾广森, 张丽, 卢聪明, 等. 内冷通道横流条件下气膜冷却特性[J]. 航空动力学报, 2015, 30(4): 823-830. Jia Guangsen, Zhang Li, Lu Congming, et al. Film cooling performance with internal coolant channel crossflow[J]. Journal of Aerospace Power, 2015, 30(4): 823-830. (in Chinese doi: 10.13224/j.cnki.jasp.2015.04.008Jia Guangsen, Zhang Li, Lu Congming, et al. Film cooling performance with internal coolant channel crossflow[J]. Journal of Aerospace Power, 2015, 30(4): 823-830. (in Chinese) doi: 10.13224/j.cnki.jasp.2015.04.008 [17] 刘存良, 宋辉, 郭涛, 等. 带肋横流进气方式下气膜孔的流阻特性与机理研究[J]. 推进技术, 2016, 37(7): 1320-1327. Liu Cunliang, Song Hui, Guo Tao, et al. Flow resistance characteristics and mechanism of film cooling holes with ribbed crossflow[J]. Journal of Propulsion Technology, 2016, 37(7): 1320-1327. (in Chinese doi: 10.13675/j.cnki.tjjs.2016.07.016Liu Cunliang, Song Hui, Guo Tao, et al. Flow resistance characteristics and mechanism of film cooling holes with ribbed crossflow[J]. Journal of Propulsion Technology, 2016, 37(7): 1320-1327. (in Chinese) doi: 10.13675/j.cnki.tjjs.2016.07.016 [18] 刘峰, 徐庆宗, 刘昊阳, 等. 外部横流下不同气膜孔型流量系数敏感性试验研究[J]. 热能动力工程, 2024, 39(11): 106-115. Liu Feng, Xu Qingzong, Liu Haoyang, et al. Experimental study on sensitivity of different film hole discharge coefficients under external crossflow conditions[J]. Journal of Engineering for Thermal Energy and Power, 2024, 39(11): 106-115. (in Chinese doi: 10.16146/j.cnki.rndlgc.2024.11.011Liu Feng, Xu Qingzong, Liu Haoyang, et al. Experimental study on sensitivity of different film hole discharge coefficients under external crossflow conditions[J]. Journal of Engineering for Thermal Energy and Power, 2024, 39(11): 106-115. (in Chinese) doi: 10.16146/j.cnki.rndlgc.2024.11.011 [19] Liu Haoyang, Du Qiang, Xu Qingzong, et al. Investigation of the discharge coefficient for laidback fan-shaped holes on turbine blades under internal crossflow condition[J]. Journal of Turbomachinery, 2025, 147: 011005. doi: 10.1115/1.4066145 [20] Hu Jiajun, An Baitao. Effects of ribbed crossflow channel in a turbine blade on film cooling performance of diffusion slot holes with various cross section orientations[J]. Journal of Turbomachinery, 2025, 147: 011003. doi: 10.1115/1.4066144 [21] 张靖周, 周君辉, 刘春丽. 内冷通道横流对气膜冷却效率的影响[J]. 南京航空航天大学学报, 2014, 46(4): 509-516. Zhang Jingzhou, Zhou Junhui, Liu Chunli. Effect of internal crossflow in coolant channel on adiabatic film cooling effectiveness[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2014, 46(4): 509-516. (in Chinese doi: 10.3969/j.issn.1005-2615.2014.04.004Zhang Jingzhou, Zhou Junhui, Liu Chunli. Effect of internal crossflow in coolant channel on adiabatic film cooling effectiveness[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2014, 46(4): 509-516. (in Chinese) doi: 10.3969/j.issn.1005-2615.2014.04.004 [22] 陈娉婷, 秦晏旻, 任静, 等. 带肋通道和气膜冷却交互下的绝热和耦合传热研究[J]. 工程热物理学报, 2016, 37(7): 1422-1426. Chen Pingting, Qin Yanmin, Ren Jing, et al. Research on the interaction of ribbed passage and film cooling in adiabatic and coupling condition[J]. Journal of Engineering Thermophysics, 2016, 37(7): 1422-1426. (in ChineseChen Pingting, Qin Yanmin, Ren Jing, et al. Research on the interaction of ribbed passage and film cooling in adiabatic and coupling condition[J]. Journal of Engineering Thermophysics, 2016, 37(7): 1422-1426. (in Chinese) [23] Saumweber C, Schulz A. Effect of geometry variations on the cooling performance of fan-shaped cooling holes[J]. Journal of Turbomachinery, 2012, 134(6): 061008. doi: 10.1115/1.4006290 [24] 蒋跃文. 基于广义网格的CFD方法及其应用 [D]. 西安: 西北工业大学, 2013. Jiang Yuewen. Methodology of generalized mesh and its application to solve the Navier-Stokes equations [D]. Xi’an: Northwestern Polytechnical University, 2013 (in ChineseJiang Yuewen. Methodology of generalized mesh and its application to solve the Navier-Stokes equations [D]. Xi’an: Northwestern Polytechnical University, 2013 (in Chinese) [25] Jiang Yuewen. General mesh method: a unified numerical scheme[J]. Computer Methods in Applied Mechanics and Engineering, 2020, 369: 113049. doi: 10.1016/j.cma.2020.113049 [26] Roe P. Characteristic-based schemes for the Euler equations[J]. Annual Review of Fluid Mechanics, 1986, 18: 337-365. doi: 10.1146/annurev.fl.18.010186.002005 [27] MENTER F, ESCH T. Elements of industrial heat transfer predictions[C]//Proceedings of the 16th Brazilian Congress of Mechanical Engineering. Minas Gerais, Brazil: ABCM, 2001: 117-127. -
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