旋流杯燃烧室头部冷却设计及其对壁温的影响

赵婷杰; 于小兵; 卢铭涛; 王柏森; 林宇震

doi:10.13224/j.cnki.jasp.20230116

旋流杯燃烧室头部冷却设计及其对壁温的影响

doi: 10.13224/j.cnki.jasp.20230116

赵婷杰^{1, 2, 3,},
于小兵¹,
卢铭涛¹,
王柏森^{2, 3},
林宇震^{2, 3}

1.
中国航发贵阳发动机设计研究所，贵阳 550081
2.
北京航空航天大学航空发动机研究院，北京 102206
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 102206

详细信息

作者简介:
赵婷杰（1988-），女，工程师，硕士，主要从事燃烧室气动设计研究。E-mail：zhaotingjie2010@163.com

中图分类号: V231.2
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出版历程
- 收稿日期: 2023-03-01
- 网络出版日期: 2023-06-12

Cooling design for head of swirl-cup combustor and its effect on wall temperature

ZHAO Tingjie^{1, 2, 3
,},
YU Xiaobing¹,
LU Mingtao¹,
WANG Bosen^{2, 3},
LIN Yuzhen^{2, 3}

1.
Guiyang Engine Design Research Institute， Aero Engine Corporation of China，Guiyang 550081，China
2.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics， Beihang University，Beijing 102206，China

摘要

摘要:
在保证燃烧室流场结构相似、流量分配相当的基础上，针对旋流杯燃烧室开展平直孔板耦合挡溅板和斜向导流孔板耦合导流护罩两种头部冷却结构的设计，通过高温高压扇形燃烧室试验和三维数值仿真对冷却性能进行评估和分析。结果表明：平直孔板耦合挡溅板冷却结构的壁温远高于斜向导流孔板耦合导流护罩冷却结构的壁温，其主要原因是斜向导流孔板耦合导流护罩冷却方式为带有一定角度的收敛双锥形冷却构型，可通过引导气流吹除燃烧室头部近壁面角涡区，防止燃气在靠近壁面处产生高温区，从而降低燃烧室头部壁温。斜向导流孔板耦合导流护罩冷却结构的壁温大幅度降低，且温度分布均匀，提高了头部的冷却性能，增强了燃烧室头部结构的可靠性。
- 燃烧室头部 /
- 冷却结构 /
- 近壁面角涡 /
- 近壁面流场和温度场 /
- 高温高压扇形试验
Abstract:
On the basis of ensuring similar flow field structure and equivalent flow distributions of the combustor, two cooling structures were designed for the head of a swirl cup combustor: a straight orifice coupled with a splash plate and an inclined flow guide orifice coupled with a guide shield. The cooling performances of the two structures were evaluated and analysed through high-temperature and high-pressure tests of fan-shaped and three-dimensional numerical simulations. Results showed that the wall temperature of the cooling structure of the straight orifice coupled with the splash plate was much higher than that of the inclined fluid guide orifice coupled with the guide shield, primarily owing to the fact that the latter one had a converging biconical cooling configuration with a certain angle which can blow off the angular vortex near the wall of the head by guiding the airflow, prevent the gas from heating up a high temperature area near the wall surface, thus reducing the wall temperature. The wall temperature of the cooling structure of the inclined guide orifice coupled with the guide shield was greatly reduced, and the temperature distribution was more uniform, which improved the cooling performance of the head and enhanced the reliability of the head structure of the combustion chamber.
- combustor head /
- cooling structure /
- near-wall angular vortex /
- near-wall flow field and temperature field /
- high temperature and high pressure test of fan-shaped

HTML

图 1 燃烧室方案示意图

Figure 1. Schematic diagram of the combustor

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图 2 直壁孔板耦合直壁挡溅板冷却结构

Figure 2. Structure of straight orifice plate couple splash plate cooling

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图 3 斜向导流环耦合导流护罩冷却结构

Figure 3. Structure of inclined orifice plate couple flow shield cooling

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图 4 扇形燃烧室试验系统

Figure 4. Test system of fan-shaped combustor

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图 5 冷却结构A火焰筒头部测点位置

Figure 5. Position of measuring point on the cooling structure A head of flame cylinder

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图 6 冷却结构B火焰筒头部测点位置

Figure 6. Position of measuring point on the cooling structure B head of flame cylinder

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图 7 燃烧室网格划分

Figure 7. Mesh generation of combustor

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图 8 距离燃烧室进口x=120 mm处轴向速度

Figure 8. Axial-direction velocity at x=120 mm from the inlet of combustor

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图 9 距离燃烧室进口x=120 mm处总温

Figure 9. Total temperature at x=120 mm from the inlet of combustor

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图 10 壁温测量结果

Figure 10. Results of wall temperature

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图 11 冷却结构A示温漆判断结果

Figure 11. Result of chameleon paint of the cooling structure A

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图 12 冷却结构B示温漆判断结果

Figure 12. Result of chameleon paint of the cooling structure B

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图 13 冷却结构A燃烧室头部速度矢量图

Figure 13. Velocity vector of the cooling structure A head of combustor

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图 14 冷却结构A局部速度矢量图

Figure 14. Local velocity vector of the cooling structure A

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图 15 冷却结构A燃烧室头部油气比分布

Figure 15. Oil-gas ratio distribution of the cooling structure A head of combustor

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图 16 冷却结构A燃烧室头部温度场

Figure 16. Temperature field of the cooling structure A head of combustor

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图 17 冷却结构B燃烧室头部速度矢量图

Figure 17. Velocity vector of the cooling structure B head of combustor

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图 18 冷却结构B局部速度矢量图

Figure 18. Local velocity vector of the cooling structure B

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图 19 冷却结构B燃烧室头部油气比分布

Figure 19. Oil-gas ratio distribution of the cooling structure B head of combustor

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图 20 冷却结构B燃烧室头部温度场

Figure 20. Temperature field of the cooling structure B head of combustor

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参考文献(21)

[1]	何小民, 张净玉, 李建中. 航空发动机燃烧室原理[M]. 北京: 北京航空航天大学出版社, 2015: 6-11.
[2]	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: 156-169.
[3]	林宏军,迟雪. 火焰筒先进热防护技术发展及工程应用分析[J]. 航空动力,2020(3): 66-70. LIN Hongjun,CHI Xue. Development and engineering application analysis of advanced thermal protection technology of flame tube[J]. Aerospace Power,2020(3): 66-70. (in Chinese)
[4]	陈亚林. 高温升燃烧室冷却方案研究[D]. 南京: 南京航空航天大学, 2013. CHEN Yalin. Research on cooling technology of high temperature rise combustor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013. (in Chinese)
[5]	许全宏,徐剑,林宇震,等. 多斜孔冷却方式气动参数对壁温梯度和冷却效率的影响[J]. 航空动力学报,2008,23(4): 647-650. XU Quanhong,XU Jian,LIN Yuzhen,et al. Influence of aerodynamic parameter on the temperature gradient and cooling efficiency for effusion wall cooling method[J]. Journal of Aerospace Power,2008,23(4): 647-650. (in Chinese)
[6]	杨谦,林宇震,张弛,等. 发散冷却与冲击/发散冷却的冷却效率对比[J]. 航空动力学报,2014,29(2): 268-276. YANG Qian,LIN Yuzhen,ZHANG Chi,et al. Cooling effectiveness comparison between effusion cooling and impingement/effusion cooling[J]. Journal of Aerospace Power,2014,29(2): 268-276. (in Chinese)
[7]	许全宏,林宇震,刘高恩. 主燃烧室冲击/发散双层壁冷却方式壁温验证试验研究[J]. 航空动力学报,2005,20(2): 197-201. XU Quanhong,LIN Yuzhen,LIU Gaoen. Rig test of impingement/effusion double wall cooling methods for the main combustor[J]. Journal of Aerospace Power,2005,20(2): 197-201. (in Chinese)
[8]	李彬,吉洪湖,江义军. 冲击-发散冷却火焰筒浮动瓦片三维壁温计算分析[J]. 航空动力学报,2007,22(3): 370-374. doi: 10.3969/j.issn.1000-8055.2007.03.007 LI Bin,JI Honghu,JIANG Yijun. Numerical analysis of 3D temperature field of an impingement-effusion cooled flame tube floating tile[J]. Journal of Aerospace Power,2007,22(3): 370-374. (in Chinese) doi: 10.3969/j.issn.1000-8055.2007.03.007
[9]	商体松,赵明,涂冰怡. 航空发动机燃烧室冷却结构的发展及浮动壁结构的关键技术[J]. 航空工程进展,2013,4(4): 407-413. SHANG Tisong,ZHAO Ming,TU Bingyi. Development of aero-engine combustor cooling structure and the key technologies of floating-wall[J]. Advances in Aeronautical Science and Engineering,2013,4(4): 407-413. (in Chinese)
[10]	徐剑,许全宏,林宇震,等. 火焰筒多斜孔冷却方式壁温梯度和冷却效率试验[J]. 航空动力学报,2008,23(3): 425-429. XU Jian,XU Quanhong,LIN Yuzhen,et al. Experimental investigation of the temperature gradient and cooling efficiency for effusion wall cooling methods on combustion liner[J]. Journal of Aerospace Power,2008,23(3): 425-429. (in Chinese)
[11]	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)
[12]	杨卫华,卢聪明,郑建文. 气膜-发散冷却结构冷却效果的实验研究[J]. 南京航空航天大学学报,2014,46(4): 517-523. YANG Weihua,LU Congming,ZHENG Jianwen. Experimental investigation on cooling effectiveness of film-effusion cooling[J]. Journal of Nanjing University of Aeronautics and Astronautics,2014,46(4): 517-523. (in Chinese)
[13]	田美,冯晓星,石蕊. 气膜-发散组合冷却结构换热特性的实验研究[J]. 推进技术,2018,39(8): 1771-1779. TIAN Mei,FENG Xiaoxing,SHI Rui,et al. Experi mental investigation on heat transfer characteristics of film-effusion combined cooling[J]. Journal of Propulsion Technology,2018,39(8): 1771-1779. (in Chinese)
[14]	林宇震,俞文利,刘高恩,等. 冲击加发散双层壁冷却方式压降分配对斜孔内对流换热影响的研究[J]. 航空学报,2003,24(2): 97-101. LIN Yuzhen,YU Wenli,LIU Gaoen,et al. Influence of pressure drop distribution on the convection heat transfer inside the inclined hole of impingement/effusion cooling[J]. Acta Aeronautica et Astronautica Sinica,2003,24(2): 97-101. (in Chinese)
[15]	BRIONES A M,STOUFFER S D,VOGIATZIS K,et al. Effects of effusion and film cooling jet momenta on combustor flow fields[J]. Journal of Engineering for Gas Turbines and Power,2018,140(8): 081503.1-081503.10.
[16]	汤朝伟. 回流燃烧室火焰筒头部导流板影响燃烧特性研究[D]. 南京: 南京航空航天大学, 2021. TANG Chaowei. Influence of the dome deflector parameters on combustion characteristics in reverse flow combustor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021. (in Chinese)
[17]	李彬,程波. 高温升火焰筒壁面及头部复合冷却设计分析[J]. 燃气涡轮试验与研究,2007,20(3): 8-10, 56. LI Bin,CHENG Bo. Design analysis for compound cooling of high temperature rise combustor wall & head shield[J]. Gas Turbine Experiment and Research,2007,20(3): 8-10, 56. (in Chinese)
[18]	党新宪,赵坚行,颜应文,等. 双旋流器燃烧室壁温试验[J]. 航空动力学报,2010,25(6): 1227-1232. DANG Xinxian,ZHAO Jianxing,YAN Yingwen,et al. Experiment of wall temperature in a two-stage swirler combustor[J]. Journal of Aerospace Power,2010,25(6): 1227-1232. (in Chinese)
[19]	张荣春,樊未军,邢菲. 环形级间驻涡燃烧室壁温分布试验[J]. 航空动力学报,2010,25(6): 1238-1244. ZHANG Rongchun,FAN Weijun,XING Fei. Experimental study of wall temperature distribution on annular interstage trapped vortex combustor[J]. Journal of Aerospace Power,2010,25(6): 1238-1244. (in Chinese)
[20]	金捷,马继华,金如山. 燃烧室室壁冲击/气膜复合冷却壁温分布研究: (一)实验部分[J]. 推进技术,1994,15(1): 14-17. JIN Jie,MA Jihua,JIN Rushan. Studies on the distribution of wall temperature of impingement and film cooling of combustion chambers: (1) experimentally[J]. Journal of Propulsion Technology,1994,15(1): 14-17. (in Chinese)
[21]	金捷,马继华,金如山. 燃烧室室壁冲击/气膜复合冷却壁温分布研究: (二)理论部分[J]. 推进技术,1994,15(2): 34-40. JIN Jie,MA Jihua,JIN Rushan. Studies on the distribution of wall temperature of impingement and film cooling of combustion chambers: (2) theoretically[J]. Journal of Propulsion Technology,1994,15(2): 34-40. (in Chinese)