背风侧倾斜开孔的非均匀布局波纹隔热屏气膜冷却特性研究

穆轶涵; 乔程雨; 刘玉英; 刘广海

doi:10.13224/j.cnki.jasp.20250011

背风侧倾斜开孔的非均匀布局波纹隔热屏气膜冷却特性研究

doi: 10.13224/j.cnki.jasp.20250011

北京航空航天大学能源与动力工程学院，北京 100191

基金项目: 国家科技重大专项（J09-Ⅲ-0016-0060）

详细信息

作者简介:
穆轶涵（2002-），男，硕士生，主要从事航空发动机热端部件冷却研究

通讯作者:
刘玉英（1974-），女，教授，博士，主要从事发动机燃烧研究。E-mail：yyliu@buaa.edu.cn

中图分类号: V231.2
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出版历程
- 收稿日期: 2025-01-07
- 网络出版日期: 2026-04-05

Study on film cooling characteristics of non-uniform layout corrugated heat shield with inclined holes on leeward side

School of Energy and Power Engineering，Beihang University，Beijing 100191，China

摘要

摘要:
针对纵向波纹隔热屏波峰处冷却效率低的问题，提出了一种仅波谷背风侧倾斜开孔的非均匀布局型纵向波纹隔热屏，基于CFD商用软件，使用流固耦合数值模拟方法，与均匀布局、疏密型布局等传统结构方案进行了对比研究，并在孔倾角为20°～40°、吹风比为0.82～1.85的情况下对隔热屏壁面冷却效果进行了分析，研究了孔倾角和吹风比对隔热屏冷却效率的影响规律。结果表明：该方案可以充分利用背风侧动压进气，能显著缩小壁面高温区，提高波峰冷却效率，同时可以改善壁面温度均匀性。孔倾角越小，波谷冷却效率越低，波峰冷却效率越高，波峰冷却效率在孔倾角为30°～35°时最高，相比基准方案提高了5.62%；在吹风比为1.85时，该方案对波峰冷却效率的提升幅度最大，相比基准方案提高了5.57%，但冷却效率均匀系数减小了7.57%。
- 加力燃烧室 /
- 纵向波纹隔热屏 /
- 气膜冷却 /
- 孔倾角 /
- 吹风比
Abstract:
To address the issue of low cooling efficiency at the crests of longitudinally corrugated heat shields, a novel structural—a non-uniformly distributed longitudinally corrugated heat shield with inclined perforations only on the leeward side of the troughs, was proposed. Using commercial CFD software and fluid-solid coupled numerical simulation methods, comparative studies were conducted with traditional structural schemes including uniformly distributed and graded-density configurations. The cooling performance of the heat shield's wall was analyzed under hole inclination angles ranging from 20° to 40° and blowing ratios between 0.82 and 1.85, and the effects of inclination angle and blowing ratio on cooling efficiency were examined. The results showed that the proposed design effectively utilized dynamic pressure intake on the leeward side, significantly reduced high-temperature zones on the wall, improved crest cooling efficiency, and enhanced wall temperature uniformity. A smaller inclination angle decreased trough cooling efficiency but increased crest cooling efficiency, with the crest cooling efficiency reaching its peak at an inclination angle of 30° to 35°, representing a 5.62% improvement compared with the baseline model. At a blowing ratio of 1.85, the maximum enhancement in crest cooling efficiency reached 5.57% compared with the baseline model, though accompanied by a 7.57% reduction in cooling efficiency uniformity coefficient.
- afterburner /
- longitudinal corrugated heat shield /
- film cooling /
- hole inclination angle /
- blowing ratio

HTML

图 1 F110发动机加力燃烧室结构示意图

Figure 1. Schematic diagram of the afterburner chamber structure in the F110 engine

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图 2 隔热屏波纹结构

Figure 2. Structure of corrugated heat shield

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图 3 波纹隔热屏结构与开孔位置

Figure 3. Structure and hole position of corrugated heat shield

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图 4 气膜孔排布

Figure 4. Film hole arrangement

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图 5 计算域（单位：mm）

Figure 5. Calculation region （unit：mm）

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图 6 约定截面名称

Figure 6. Agreed section names

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图 7 流固交界处及气膜孔处y⁺云图

Figure 7. y⁺ contour plot at fluid-solid interface and film cooling holes

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图 8 不同网格计算结果

Figure 8. Calculation results of different grids

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图 9 文献[13]的实验系统及模型

Figure 9. Experimental system and model from Ref. [13]

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图 10 实验与数值结果对比

Figure 10. Comparison of numerical and experimental results

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图 11 不同方案隔热屏沿程展向平均冷却效率

Figure 11. Laterally-averaged cooling efficiency along the streamwise of different schemes

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图 12 不同方案速度分布与流线

Figure 12. Velocity distribution and streamline of different schemes

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图 13 不同方案壁面努塞尔数

Figure 13. Wall Nusselt number of different schemes

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图 14 Case 0与Case 4的展向平均努塞尔数对比

Figure 14. Laterally-averaged Nusselt number comparison between Case 0 and Case 4

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图 15 孔倾角对速度分布与流线的影响

Figure 15. Influence of hole inclination angle on velocity distribution and streamline

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图 16 孔倾角对沿程展向平均冷却效率的影响

Figure 16. Influence of hole inclination angle on laterally-averaged cooling efficiency along the streamwise

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图 17 孔倾角对隔热屏壁面温度分布的影响

Figure 17. Influence of hole inclination angle on distribution of wall temperature of heatshield

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图 18 孔倾角对第5周期波峰平均冷却效率的影响

Figure 18. Influence of hole inclination angle on peak averaged cooling efficiency of fifth period

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图 19 孔倾角对第6周期波峰平均冷却效率的影响

Figure 19. Influence of hole inclination angle on peak averaged cooling efficiency of sixth period

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图 20 孔倾角对冷却效率均匀系数的影响

Figure 20. Influence of hole inclination angle on cooling effectiveness deviation

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图 21 孔倾角对总压恢复系数影响

Figure 21. Influence of hole inclination angle on total pressure recovery coefficient

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图 22 吹风比对隔热屏壁面温度分布的影响

Figure 22. Influence of blowing ratio on distribution of wall temperature of heatshield

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图 23 吹风比对Case 4中Plane 1截面速度分布与流线的影响

Figure 23. Influence of blowing ratio on velocity distribution and streamline for cross-section Plane 1 in Case 4

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图 24 吹风比对沿程展向平均冷却效率的影响

Figure 24. Influence of blowing ratio on laterally-averaged cooling efficiency along the streamwise

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图 25 吹风比对波峰平均冷却效率的影响

Figure 25. Influence of blowing ratio on peak averaged cooling efficiency

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图 26 吹风比对冷却效率均匀系数的影响

Figure 26. Influence of blowing ratio on cooling effectiveness deviation

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表 1 边界条件

Table 1. Boundary conditions

参数	数值
次流入口质量流量$ {\dot{m}}_{\text{cin}} $/（kg/s）	0.00733
主流入口质量流量$ {\dot{m}}_{\text{hin}} $/（kg/s）	0.04199
次流出口质量流量$ {\dot{m}}_{\text{cout}} $/（kg/s）	0.005352
次流入口温度T_c/K	485.6
主流入口温度T_h/K	2100

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表 2 不同孔倾角方案结构参数

Table 2. Structure parameters of different hole inclination angle schemes

方案	孔径d/mm	孔倾角α/（°）	开孔方式
Case 0	0.4	90	垂直
Case 4-20°	0.61	20	倾斜
Case 4-25°	0.61	25	倾斜
Case 4-30°	0.61	30	倾斜
Case 4-35°	0.61	35	倾斜
Case 4-40°	0.61	40	倾斜
Case 3	0.61	90	垂直

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表 3 不同吹风比方案结构参数

Table 3. Structure parameters of different blowing ratio schemes

方案	孔径d/mm	孔倾角α/（°）	M
Case 0-M1.85	0.4	90	1.85
Case 4-α35-M1.85	0.61	35	1.85
Case 0-M1.46	0.45	90	1.46
Case 4-α35-M1.46	0.69	35	1.46
Case 0-M1.18	0.5	90	1.18
Case 4-α35-M1.18	0.76	35	1.18
Case 0-M0.82	0.6	90	0.82
Case 4-α35-M0.82	0.92	35	0.82

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参考文献(27)

[1]	黄勇, 林宇震, 樊未军, 等. 燃烧与燃烧室[M]. 北京: 北京航空航天大学出版社, 2009.
[2]	季鹤鸣. 第四代歼击机发动机加力燃烧室的技术特点[J]. 航空发动机, 1996, 22(4): 3-12. Ji Heming. Technical characteristics of afterburner of the fourth generation fighter engine[J]. Aeroengine, 1996, 22(4): 3-12. (in Chinese Ji Heming. Technical characteristics of afterburner of the fourth generation fighter engine[J]. Aeroengine, 1996, 22(4): 3-12. (in Chinese)
[3]	Andrews G E, Asere A A, Gupta M L, et al. Full coverage discrete hole film cooling: the influence of hole size[R]. Houston, US: ASME 1985 International Gas Turbine Conference and Exhibit, 1985.
[4]	Mobgia H C, Reide S B. Allison combustion research and development activities[R]. AIAA-85-21402, 1985.
[5]	Qu Lihong, Zhang Jingzhou, Tan Xiaoming, et al. Numerical investigation on adiabatic film cooling effectiveness and heat transfer coefficient for effusion cooling over a transverse corrugated surface[J]. Chinese Journal of Aeronautics, 2017, 30(2): 677-684. doi: 10.1016/j.cja.2017.02.012
[6]	王敏敏, 赵熙, 林莉, 等. 纵向波纹隔热屏气膜冷却特性实验[J]. 航空动力学报, 2019, 34(12): 2648-2655. Wang Minmin, Zhao Xi, Lin Li, et al. Experiment on film cooling characteristics for longitudinal corrugated heat-shield[J]. Journal of Aerospace Power, 2019, 34(12): 2648-2655. (in Chinese doi: 10.13224/j.cnki.jasp.2019.12.014 Wang Minmin, Zhao Xi, Lin Li, et al. Experiment on film cooling characteristics for longitudinal corrugated heat-shield[J]. Journal of Aerospace Power, 2019, 34(12): 2648-2655. (in Chinese) doi: 10.13224/j.cnki.jasp.2019.12.014
[7]	Niu Jiajia, Liu Cunliang, Fu Song, et al. Experiment investigation of impingement/effusion cooling on overall cooling effectiveness and temperature gradients of afterburner heat shields in a high-performance aircraft engine[J]. Experimental Thermal and Fluid Science, 2022, 139: 110698. doi: 10.1016/j.expthermflusci.2022.110698
[8]	张孝春, 孙雨超, 刘涛. 先进加力燃烧室设计技术综述[J]. 航空发动机, 2014, 40(2): 24-30, 60. Zhang Xiaochun, Sun Yuchao, Liu Tao. Summary of advanced afterburner design technology[J]. Aeroengine, 2014, 40(2): 24-30, 60. (in Chinese doi: 10.13477/j.cnki.aeroengine.2014.02.006 Zhang Xiaochun, Sun Yuchao, Liu Tao. Summary of advanced afterburner design technology[J]. Aeroengine, 2014, 40(2): 24-30, 60. (in Chinese) doi: 10.13477/j.cnki.aeroengine.2014.02.006
[9]	王敏敏, 单勇, 李江宁, 等. 纵向波纹隔热屏气膜冷却特性数值研究[J]. 推进技术, 2016, 37(8): 1535-1542. Wang Minmin, Shan Yong, Li Jiangning, et al. Numerical study on film cooling characteristics for longitudinal ripple heat shield in afterburner[J]. Journal of Propulsion Technology, 2016, 37(8): 1535-1542. (in Chinese doi: 10.13675/j.cnki.tjjs.2016.08.018 Wang Minmin, Shan Yong, Li Jiangning, et al. Numerical study on film cooling characteristics for longitudinal ripple heat shield in afterburner[J]. Journal of Propulsion Technology, 2016, 37(8): 1535-1542. (in Chinese) doi: 10.13675/j.cnki.tjjs.2016.08.018
[10]	唐婵, 常海萍. 发散孔纵向波纹隔热屏气膜冷却特性[J]. 航空动力学报, 2009, 24(1): 18-24. Tang Chan, Chang Haiping. Numerical simulation of effusion holes on the longitudinal ripple heat shield[J]. Journal of Aerospace Power, 2009, 24(1): 18-24. (in Chinese doi: 10.3969/j.issn.1009-2889.2009.01.009 Tang Chan, Chang Haiping. Numerical simulation of effusion holes on the longitudinal ripple heat shield[J]. Journal of Aerospace Power, 2009, 24(1): 18-24. (in Chinese) doi: 10.3969/j.issn.1009-2889.2009.01.009
[11]	Singh K, Premachandran B, Ravi M R. Experimental and numerical studies on film cooling of a corrugated surface[J]. Applied Thermal Engineering, 2016, 108: 312-329. doi: 10.1016/j.applthermaleng.2016.07.093
[12]	Ren Haoliang, Liu Youhong. Experimental investigation of fluid flow and heat transfer characteristics of a longitudinal corrugated liner for a combustion chamber[J]. Applied Thermal Engineering, 2016, 108: 1066-1075. doi: 10.1016/j.applthermaleng.2016.08.015
[13]	常国强, 常海萍, 常飞, 等. 多孔纵向波纹表面气膜冷却效率实验研究[J]. 航空动力学报, 2009, 24(3): 513-518. Chang Guoqiang, Chang Haiping, Chang Fei, et al. Experimental investigation on film cooling effectiveness of multi-hole at longitudinal wavy surface[J]. Journal of Aerospace Power, 2009, 24(3): 513-518. (in Chinese Chang Guoqiang, Chang Haiping, Chang Fei, et al. Experimental investigation on film cooling effectiveness of multi-hole at longitudinal wavy surface[J]. Journal of Aerospace Power, 2009, 24(3): 513-518. (in Chinese)
[14]	常飞. 纵向波纹隔热屏局部流动与换热特性数值分析[D]. 南京: 南京航空航天大学, 2009. Chang Fei. Numerical simulation on the characteristic of flow and heat transfer in longitudinal ripple way liner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2009. (in Chinese Chang Fei. Numerical simulation on the characteristic of flow and heat transfer in longitudinal ripple way liner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2009. (in Chinese)
[15]	Napoli P D. Combustor liner with circumferentially angled film cooling holes: US5233828[P]. 1993-08-10.
[16]	Champion J L, Deshaies B, Curtelin R, et al. Aerodynamical structure of the wall flow over a wavy surface partially cooled by air injection through multiperforations[R]. AIAA-1999-1016, 1999.
[17]	刘海涌, 牛嘉嘉, 刘存良, 等. 开孔率对加力燃烧室隔热屏冷却特性的影响[J]. 航空发动机, 2022, 48(6): 64-70. Liu Haiyong, Niu Jiajia, Liu Cunliang, et al. Influence of open area on cooling characteristics of afterburner liner[J]. Aeroengine, 2022, 48(6): 64-70. (in Chinese doi: 10.13477/j.cnki.aeroengine.2022.06.010 Liu Haiyong, Niu Jiajia, Liu Cunliang, et al. Influence of open area on cooling characteristics of afterburner liner[J]. Aeroengine, 2022, 48(6): 64-70. (in Chinese) doi: 10.13477/j.cnki.aeroengine.2022.06.010
[18]	Nicoll R A, Vdoviak J W. Multi-hole film cooled afterburner combustor liner: US5465572[P]. 1995-11-14.
[19]	王敏敏. 纵向波纹隔热屏气膜冷却特性研究[D]. 南京: 南京航空航天大学, 2016. Wang Minmin. Numerical study on the film cooling characteristics for the longitudinal ripple heat shield in the afterburner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese Wang Minmin. Numerical study on the film cooling characteristics for the longitudinal ripple heat shield in the afterburner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese)
[20]	曾文明. 高冷气温度下隔热屏气膜冷却特性研究[D]. 南京: 南京航空航天大学, 2019. Zeng Wenming. Study on film cooling characteristics of heat shield with high-temperature coolant[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese Zeng Wenming. Study on film cooling characteristics of heat shield with high-temperature coolant[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese)
[21]	梁喜源, 刘海涌, 白晓辉, 等. 冷却孔非均匀排布波纹板隔热屏冷却特性仿真[J]. 航空发动机, 2023, 49(4): 26-31, F0002. Liang Xiyuan, Liu Haiyong, Bai Xiaohui, et al. Simulation of cooling characteristics of corrugated heat shield with non-uniformly disposed cooling holes[J]. Aeroengine, 2023, 49(4): 26-31, F0002. (in Chinese doi: 10.13477/j.cnki.aeroengine.2023.04.004 Liang Xiyuan, Liu Haiyong, Bai Xiaohui, et al. Simulation of cooling characteristics of corrugated heat shield with non-uniformly disposed cooling holes[J]. Aeroengine, 2023, 49(4): 26-31, F0002. (in Chinese) doi: 10.13477/j.cnki.aeroengine.2023.04.004
[22]	朱惠人, 徐志鹏, 张丽, 等. 一种用于波纹隔热屏的偏置孔排加圆柱孔排组合冷却结构: CN112178693[P]. 2022-04-19.
[23]	Wang Ziwen, Bai Xiaohui, Liu Haiyong, et al. Study on flow structure and heat transfer characteristics of a novel double layer heat shield in an afterburner[J]. Thermal Science and Engineering Progress, 2024, 48: 102353. doi: 10.1016/j.tsep.2023.102353
[24]	Shih T H, Liou W W, Shabbir A, et al. A new k-ε eddy viscosity model for high Reynolds number turbulent flows[J]. Computers & Fluids, 1995, 24(3): 227-238. doi: 10.1016/0045-7930(94)00032-T
[25]	Xu Z P, Zhu H R, Wang Y Z, et al. Numerical study on flow and heat transfer characteristics of discrete film cooling holes of the sinusoidal longitudinal corrugated heat liner[R]. Phoenix, US: ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, 2019.
[26]	渠立红. 壁面波纹结构和主流压力梯度对发散冷却的影响[D]. 南京: 南京航空航天大学, 2018. Qu Lihong. Effects of corrugated wall structure and streamwise pressure gradient on effusion cooling performances[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2018. (in Chinese Qu Lihong. Effects of corrugated wall structure and streamwise pressure gradient on effusion cooling performances[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2018. (in Chinese)
[27]	《中国航空材料手册》编辑委员会. 中国航空材料手册第1卷: 结构钢不锈钢[M]. 2版. 北京: 中国标准出版社, 2002: 278-279.