类椭圆形CMC火焰筒多斜孔冷却性能数值分析

于国强; 隋正卿; 陈正扬; 倪政; 杜金康; 高希光; 宋迎东

doi:10.13224/j.cnki.jasp.20230084

类椭圆形CMC火焰筒多斜孔冷却性能数值分析

doi: 10.13224/j.cnki.jasp.20230084

1.
南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，南京 210016
2.
南京航空航天大学机械结构力学及控制国家重点实验室，南京 210016

基金项目: 国家科技重大专项（2017-Ⅳ-0005-0042）；国家自然科学基金（12202186）；江苏省自然科学基金（BK20210272）

详细信息

作者简介:
于国强（1990-），男，副研究员，博士，主要从事航空发动机结构强度研究

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2023-02-17
- 网络出版日期: 2024-03-20

Numerical analysis on cooling performance of quasi-elliptic multi-inclined holes in CMC combustion liner

1.
Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
State Key Laboratory of Mechanics and Control of Mechanical Structures，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为了提高陶瓷基复合材料火焰筒壁面的冷却性能，在现有的圆形多斜孔冷却结构的基础上，设计了一种新型类椭圆形多斜孔冷却结构。同时，采用三维数值模拟的方法将两种多斜孔结构的冷却效果进行了对比。结果表明：新型类椭圆斜孔特征模拟件相较于圆孔特征模拟件，壁面高温区域明显变窄，高温热斑减少，温度分布更加均匀；在经纱方向，类椭圆斜孔特征模拟件高应力区域减少，应力集中现象减弱；在纬纱方向，类椭圆斜孔特征模拟件与圆孔特征模拟件均存在高应力区域。
- 冷却结构 /
- 类椭圆斜孔 /
- 陶瓷基复合材料 /
- 火焰筒 /
- 孔阵排列
Abstract:
In order to improve the cooling performance of ceramic matrix composite combustion liner wall, a new quasi-elliptic multi-inclined hole cooling structure was designed on the basis of the existing circular multi-inclined hole cooling structure. Meanwhile, the cooling effects of two kinds of multi-inclined hole structures were compared by using three-dimensional numerical simulation method. The results showed that: compared with the circular hole feature simulator, the high temperature area on the wall of the new quasi-elliptic inclined hole simulated part was obviously narrower, the hot spots at high temperature were reduced, and the temperature distribution was more uniform. In the warp yarn direction, the high stress area of the simulated part with quasi-elliptic inclined hole features was reduced, and the stress concentration phenomenon was weakened. In the weft yarn direction, the high stress regions in the feature simulators of quasi-elliptic inclined hole and circular hole were found.
- cooling structure /
- quasi-elliptic inclined hole /
- ceramic matrix composites /
- combustion liner /
- hole arrangement

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图 1 类椭圆斜孔外形

Figure 1. Shape of quasi-elliptic inclined hole

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图 2 叉排排列方式

Figure 2. Staggered arrangement

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图 3 新型排列方式

Figure 3. New arrangement

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图 4 倾斜角示意图

Figure 4. Schematic diagram of inclination angle

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图 5 类椭圆斜孔三视图

Figure 5. Three views of quasi-elliptic inclined hole

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图 6 CMC火焰筒特征模拟件（圆孔）

Figure 6. CMC simulation specimen of combustion liner （circular hole）

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图 7 CMC火焰筒特征模拟件（类椭圆斜孔）

Figure 7. CMC simulation specimen of combustion liner （quasi-elliptic inclined hole）

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图 8 试验箱示意图

Figure 8. Schematic diagram of simulation mode

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图 9 试验箱流体域模型

Figure 9. Fluid domain model of test chamber

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图 10 网格质量数据分布图

Figure 10. Distribution graph of mesh quality data

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图 11 SiC_f/SiC_m纱线方向热膨胀系数随温度的变化

Figure 11. Change of SiC_f/SiC_m yarn direction coefficient of thermal expansion with temperature

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图 12 CMC试验箱中心截面流线图

Figure 12. Streamline diagram of center section of CMC test chamber

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图 13 CMC火焰筒特征模拟件温度分布对比

Figure 13. Comparison of temperature distribution of CMC combustion liner-like simulating specimen

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图 14 CMC火焰筒特征模拟件经纱方向应力云图

Figure 14. Stress distribution in warp yarn direction of CMC combustion liner-like simulating specimen

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图 15 CMC火焰筒特征模拟件纬纱方向应力云图

Figure 15. Stress distribution in weft yarn direction of CMC combustion liner-like simulating specimen

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图 16 CMC火焰筒特征模拟件平面剪应力云图

Figure 16. Plane shear stress distribution of CMC combustion liner-like simulating specimen

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表 1 气膜孔结构参数

Table 1. Structure parameters of film cooling holes

特征模拟件类型	D/mm	L/mm	α/（°）	β/（°）	H/P	D_p/mm
类椭圆斜孔	0.3	0.6	45	45	0.25	9.5
圆孔	0.6	0	45	0	0.50	9.5

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表 2 CMC弹性参数

Table 2. CMC elasticity parameters

参数	数值	参数	数值
E_CMC,X/GPa	227.4	μ_CMC,ZX	0.15
E_CMC,Y/GPa	227.4	G_CMC,XY/GPa	91.0
E_CMC,Z/GPa	50.0	G_CMC,YZ/GPa	17.7
μ_CMC,XY	0.15	G_CMC,ZX/GPa	17.7
μ_CMC,YZ	0.15
注：表中E_CMC、μ_CMC、G_CMC分别为CMC的拉伸模量、泊松比和切变模量。

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表 3 模型系数

Table 3. Model coefficients

参数	数值
σ_k	1.0
σ_ε	1.2
C₂	1.9

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表 4 不同火焰筒特征模拟件表面最大应力

Table 4. Maximum surface stress of different combustion liner-like simulating specimen MPa

特征模拟件类型	σ_X,max	σ_Y,max	τ_XY,max
圆孔	164	167	88.6
类椭圆斜孔	174	162	118

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表 5 SiC_f/SiC_m材料的强度极限参数

Table 5. Strength limit parameters of SiC_f/SiC_m MPa

参数	数值
X_t	220.19
Y_t	220.19
S	157.58

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参考文献(18)

[1]	林宇震,许全宏,刘高恩. 燃气轮机燃烧室[M]. 北京: 国防工业出版社,2008. LIN Yuzhen,XU Quanhong,LIU Gaoen. Cas turbine combustor[M]. Beijing: National Defense Industry Press,2008. (in Chinese LIN Yuzhen, XU Quanhong, LIU Gaoen. Cas turbine combustor[M]. Beijing: National Defense Industry Press, 2008. (in Chinese)
[2]	LEFEBVRE A H,HERBERT M V. Heat-transfer processes in gas-turbine combustion chambers[J]. Proceedings of the Institution of Mechanical Engineers,1960,174(1): 463-478. doi: 10.1243/PIME_PROC_1960_174_039_02
[3]	尉曙明. 先进燃气轮机燃烧室设计研发[M]. 上海: 上海交通大学出版社,2014. YU Shuming. Advanced gas turbine combustor design and development[M]. Shanghai: Shanghai Jiao Tong University Press,2014. (in Chinese YU Shuming. Advanced gas turbine combustor design and development[M]. Shanghai: Shanghai Jiao Tong University Press, 2014. (in Chinese)
[4]	陈焱. 致密微孔壁复合冷却数值模拟与实验研究[D]. 南京: 南京航空航天大学,2005. CHEN Yan. Numerical and experimental study of effusion cooling of a plate with compact tiny holes[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2005. (in Chinese CHEN Yan. Numerical and experimental study of effusion cooling of a plate with compact tiny holes[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005. (in Chinese)
[5]	李志强,田涛,陈钦. 多斜孔火焰筒壁冷却结构的数值模拟[J]. 北京航空航天大学学报,2008,34(10): 1204-1209. LI Zhiqiang,TIAN Tao,CHEN Qin. Numerical simulations of flame tube cooling structure with multi-jet holes[J]. Journal of Beijing University of Aeronautics and Astronautics,2008,34(10): 1204-1209. (in Chinese LI Zhiqiang, TIAN Tao, CHEN Qin. Numerical simulations of flame tube cooling structure with multi-jet holes[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(10): 1204-1209. (in Chinese)
[6]	刘江涛,吴海玲,陶涛,等. 斜孔气膜冷却数值模拟分析[J]. 工程热物理学报,2004,25(6): 1034-1036. LIU Jiangtao,WU Hailing,TAO Tao,et al. Numerical simulation of film cooling[J]. Journal of Engineering Thermophysics,2004,25(6): 1034-1036. (in Chinese LIU Jiangtao, WU Hailing, TAO Tao, et al. Numerical simulation of film cooling[J]. Journal of Engineering Thermophysics, 2004, 25(6): 1034-1036. (in Chinese)
[7]	李军,董志锐,林宇震,等. 多斜孔气膜冷却壁表面换热系数实验研究[J]. 推进技术,2000,21(5): 45-48. LI Jun,DONG Zhirui,LIN Yuzhen,et al. Experimental investigation of heat transfer coefficients on the inclined multihole film cooling wall[J]. Journal of Propulsion Technology,2000,21(5): 45-48. (in Chinese LI Jun, DONG Zhirui, LIN Yuzhen, et al. Experimental investigation of heat transfer coefficients on the inclined multihole film cooling wall[J]. Journal of Propulsion Technology, 2000, 21(5): 45-48. (in Chinese)
[8]	刘常春,吉洪湖,杨芳芳,等. 孔阵排列和偏转角对多斜孔壁火焰筒冷却效果的影响研究[J]. 推进技术,2013,34(10): 1369-1375. LIU Changchun,JI Honghu,YANG Fangfang,et al. Numerical study on cooling effects of hole arrangement and deflected angle of inclined multi-hole on annular flame tube[J]. Journal of Propulsion Technology,2013,34(10): 1369-1375. (in Chinese LIU Changchun, JI Honghu, YANG Fangfang, et al. Numerical study on cooling effects of hole arrangement and deflected angle of inclined multi-hole on annular flame tube[J]. Journal of Propulsion Technology, 2013, 34(10): 1369-1375. (in Chinese)
[9]	李玉龙,洪智亮. 国外航空发动机火焰筒材料工艺现状与趋势[J]. 航空制造技术,2021,64(14): 87-94. LI Yulong,HONG Zhiliang. Current situation and prospect on material and manufacture process of foreign aero-engine combustion liner[J]. Aeronautical Manufacturing Technology,2021,64(14): 87-94. (in Chinese LI Yulong, HONG Zhiliang. Current situation and prospect on material and manufacture process of foreign aero-engine combustion liner[J]. Aeronautical Manufacturing Technology, 2021, 64(14): 87-94. (in Chinese)
[10]	左平,何爱杰,李万福,等. 连续纤维增韧陶瓷基复合材料的发展及在航空发动机上的应用[J]. 燃气涡轮试验与研究,2019,32(5): 47-52. ZUO Ping,HE Aijie,LI Wanfu,et al. Application of continuous fiber reinforced ceramic matrix composites on aero-engine[J]. Gas Turbine Experiment and Research,2019,32(5): 47-52. (in Chinese ZUO Ping, HE Aijie, LI Wanfu, et al. Application of continuous fiber reinforced ceramic matrix composites on aero-engine[J]. Gas Turbine Experiment and Research, 2019, 32(5): 47-52. (in Chinese)
[11]	周明,杨青峰,张洪玉. 航空涡轮叶片气膜冷却孔激光加工技术进展[J]. 中国基础科学,2016,18(5): 35-42. ZHOU Ming,YANG Qingfeng,ZHANG Hongyu. Advances in laser fabrication of the aeroengine blades’ film cooling holes[J]. China Basic Science,2016,18(5): 35-42. (in Chinese doi: 10.3969/j.issn.1009-2412.2016.05.004 ZHOU Ming, YANG Qingfeng, ZHANG Hongyu. Advances in laser fabrication of the aeroengine blades’ film cooling holes[J]. China Basic Science, 2016, 18(5): 35-42. (in Chinese) doi: 10.3969/j.issn.1009-2412.2016.05.004
[12]	YANG Xing,LIU Zhao,FENG Zhenping. Numerical evaluation of novel shaped holes for enhancing film cooling performance[J]. Journal of Heat Transfer,2015,137: 071701. doi: 10.1115/1.4029817
[13]	OKITA Y,NISHIURA M. Film effectiveness performance of an arrowhead-shaped film-cooling hole geometry[J]. Journal of Turbomachinery,2007,129(2): 331-339. doi: 10.1115/1.2437781
[14]	LEE K D,KIM K Y. Performance evaluation of a novel film-cooling hole[J]. Journal of Heat Transfer,2012,134(10): 101702. doi: 10.1115/1.4006752
[15]	SARGISON J E,GUO S M,OLDFIELD M L G,et al. A converging slot-hole film-cooling geometry: Part 1 low-speed flat-plate heat transfer and loss[J]. Journal of Turbomachinery,2002,124(3): 453-460. doi: 10.1115/1.1459735
[16]	罗绍文,黄晓霞,赵宁波,等. 燃烧室壁面冷却特性数值模拟[J]. 热能动力工程,2020,35(4): 92-98. LUO Shaowen,HUANG Xiaoxia,ZHAO Ningbo,et al. Numerical simulation of cooling characteristics of combustion chamber wall[J]. Journal of Engineering for Thermal Energy and Power,2020,35(4): 92-98. (in Chinese LUO Shaowen, HUANG Xiaoxia, ZHAO Ningbo, et al. Numerical simulation of cooling characteristics of combustion chamber wall[J]. Journal of Engineering for Thermal Energy and Power, 2020, 35(4): 92-98. (in Chinese)
[17]	吴超. 湍流燃烧模型在燃烧室数值计算中的应用研究[D]. 沈阳: 沈阳航空工业学院,2009. WU Chao. Study on application of turbulent combustion model in the numerical calculation of combustor[D]. Shenyang: Shenyang Institute of Aeronautical Technology,2009. (in Chinese WU Chao. Study on application of turbulent combustion model in the numerical calculation of combustor[D]. Shenyang: Shenyang Institute of Aeronautical Technology, 2009. (in Chinese)
[18]	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.