Effect of fuel spray on combustion characteristics of a small engine annular reverse flow combustor
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摘要:
为研究燃油喷雾特性对某小发环形回流燃烧室主燃区燃烧特性的影响，采用数值模拟的方法，对环涡形燃烧室内燃油喷嘴伸入火焰筒的深度和喷雾偏转角度对燃烧室内的三维两相喷雾、燃烧特性进行了研究。结果表明：喷嘴位置和角度的变化，会导致燃油雾化性能的变化，从而引起燃烧特性的变化；随着喷嘴伸入火焰筒的深度变短，会导致高温区变窄且靠近火焰筒外壁，深度变长则会导致主燃区高温区减小且燃烧不充分；喷雾偏转角度顺时针旋转可使燃油在主燃区燃烧得更加充分。
Abstract:In order to study the effect of fuel spray on the combustion characteristics of primary combustion zone of a small engine annular reverse flow combustor, numerical simulation method was used to study the three-dimensional two-phase spray and combustion characteristics of the annular reverse flow combustor by the insertion depth of the nozzle into the flame tube and spray deflection angle in the combustor. The results showed that: the change of nozzle position and angle caused the change of fuel atomization performance, which caused the change of combustion characteristics; as the depth of nozzle extending into the flame tube became shorter, it could make the high temperature zone narrow and close to the outer wall of the flame tube. The longer depth could lead to reduction of the high temperature zone of primary combustion zone and insufficient combustion; the clockwise rotation of the spray deflection angle can make the fuel burning more fully in the primary combustion zone.
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图 4 主燃孔区域轴向和径向速度分布
Figure 4. Axial and radial velocity distribution in the primary combustion hole region
图 5 基准方案主燃孔轴向截面流线图
Figure 5. Streamline diagram of axial section of primary combustion hole in reference scheme
图 9 喷嘴伸入火焰筒深度对流场影响
Figure 9. Effect of the insertion depth of the nozzle into the flame tube on flow field
图 10 喷嘴伸入火焰筒深度对燃油颗粒轨迹影响
Figure 10. Effect of the insertion depth of the nozzle into the flame tube on fuel particle track
图 11 喷嘴伸入火焰筒深度对燃油雾化特性影响
Figure 11. Effect of the insertion depth of the nozzle into the flame tube on fuel atomization characteristics
图 12 喷嘴伸入火焰筒深度对主燃孔轴向截面温度分布影响
Figure 12. Effect of the insertion depth of the nozzle into the flame tube on temperature distribution on axial section of primary combustion hole
图 13 喷嘴伸入火焰筒深度对轴向温度分布影响
Figure 13. Effect of the insertion depth of the nozzle into the flame tube on axial temperature distribution
图 14 喷嘴伸入火焰筒深度对头部温度分布影响
Figure 14. Effect of the insertion depth of the nozzle into the flame tube on temperature distribution of head
图 16 喷雾偏转角度对燃油颗粒轨迹影响
Figure 16. Effect of spray deflection angle on fuel particle track
图 17 喷雾偏转角度对燃油雾化特性影响
Figure 17. Effect of spray deflection angle on fuel atomization characteristics
图 18 喷雾偏转角度对主燃孔轴向截面温度分布影响
Figure 18. Effect of spray deflection angle on temperature distribution on axial section of primary combustion hole
图 19 喷雾偏转角度对轴向温度分布影响
Figure 19. Effect of spray deflection angle on axial temperature distribution
图 20 喷雾偏转角度对头部温度分布影响
Figure 20. Effect of spray deflection angle on temperature distribution of head
表 1 计算方案
Table 1. Calculation programme
方案 喷嘴伸入火焰筒
深度调整/mm喷嘴偏转角度调整/（°） 0 0 0 1 −5 0 2 −1 0 3 1 0 4 5 0 5 0 5 6 0 1 7 0 −1 8 0 −5 
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[1] 李概奇, 曹俊. 先进小发燃烧室的特点和关键技术分析[C]//中国航空学会21世纪航空动力发展研讨会讨论集. 北京: 中国航空学会, 2000: 205-211. [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. [3] 李概奇,赖寿昌,严传俊. 某小型发动机环形回流燃烧室流场的数值计算[J]. 航空动力学报,1997,12(1): 71-74,109.LI Gaiqi,LAI Shouchang,YAN Chuanjun. Numerical calculation of flow field inside a small engine annular reverse-flow combustor[J]. Journal of Aerospace Power,1997,12(1): 71-74,109. (in Chinese) [4] 王梅娟,成胜军,宋双文,等. 燃烧室进口流场对某回流燃烧室性能影响的数值计算[J]. 航空动力学报,2018,33(6): 1281-1289.WANG Meijuan,CHENG Shengjun,SONG Shuangwen,et al. Numerical simulation on influence of flow field of combustor inlet on a certain reversed-flow combustor performance[J]. Journal of Aerospace Power,2018,33(6): 1281-1289. (in Chinese) [5] 赵硕,黄章芳,成胜军. 进气对某回流燃烧室性能影响的试验[J]. 航空动力学报,2015,30(6): 1293-1297.ZHAO Shuo,HUANG Zhangfang,CHENG Shengjun. Experiment on effect of inlet airflow on performance of a reverse-flow combusor[J]. Journal of Aerospace Power,2015,30(6): 1293-1297. (in Chinese) [6] 翟维阔,胡阁,彭剑勇,等. 回流燃烧室流动特性试验[J]. 航空动力学报,2019,34(10): 2081-2090.ZHAI Weikuo,HU Ge,PENG Jianyong,et al. Experiment on flow characteristics of a reverse-flow combustor[J]. Journal of Aerospace Power,2019,34(10): 2081-2090. (in Chinese) [7] 雷雨冰,胡好生,赵坚行. 环形回流燃烧室两相反应流场的数值研究[J]. 航空动力学报,2001,16(4): 350-354. doi: 10.3969/j.issn.1000-8055.2001.04.011LEI Yubing,HU Haosheng,ZHAO Jianxing. Numerical study of two phase reacting flow in annual reversed combustor[J]. Journal of Aerospace Power,2001,16(4): 350-354. (in Chinese) doi: 10.3969/j.issn.1000-8055.2001.04.011 [8] 胡好生,蔡文祥,赵坚行,等. 回流燃烧室燃烧过程的三维数值模拟[J]. 航空动力学报,2008,23(3): 454-459.HU Haosheng,CAI Wenxiang,ZHAO Jianxing,et al. Numerical simulation of three-dimensional combustion flows in annular reversed combustor[J]. Journal of Aerospace Power,2008,23(3): 454-459. (in Chinese) [9] 蔡文祥,赵坚行,胡好生,等. 数值研究环形回流燃烧室紊流燃烧流场[J]. 航空动力学报,2010,25(5): 993-998.CAI Wenxiang,ZHAO Jianxing,HU Haosheng,et al. Numerical research of turbulent combustion in reversed-type annular combustor[J]. Journal of Aerospace Power,2010,25(5): 993-998. (in Chinese) [10] 颜应文,李红红,赵坚行,等. 双环预混旋流低污染燃烧室数值研究[J]. 航空动力学报,2009,24(9): 1923-1929.YAN Yingwen,LI Honghong,ZHAO Jianxing,et al. Numerical study of low emissions for twin annular premixing swirler combustor[J]. Journal of Aerospace Power,2009,24(9): 1923-1929. (in Chinese) [11] 王文波,岳明,杜春雨,等. 喷嘴损伤对环形回流燃烧室性能的影响[J]. 航空动力学报,2017,32(6): 1335-1341.WANG Wenbo,YUE Ming,DU Chunyu,et al. Effect of nozzle damage on performance of annular backflow combustor[J]. Journal of Aerospace Power,2017,32(6): 1335-1341. (in Chinese) [12] 熊庆荣,李小柱. 回流燃烧室燃油雾化分析[J]. 弹箭与制导学报,2009,29(1): 188-190.XIONG Qingrong,LI Xiaozhu. Atomization analysis of fuel for circumfluence combustor[J]. Journal of Projectiles, Rockets, Missiles and Guidance,2009,29(1): 188-190. (in Chinese) [13] ČÍŽEK P, JÍCHA M. Re-designing annular combustor of APU for better air management and spray development[C]//Proceedings of the ASME Turbo Expo 2000: Power for Land, Sea, and Air. Munich, Germany: ASME, 2000: 1-8. [14] 李东杰. 大型民机辅助动力装置关键技术[C]//大型飞机关键技术高层论坛暨中国航空学会2007年学术年会论文集. 北京: 中国航空学会, 2007: 1054-1058. [15] MONGIA H, REYNOLDS R, COLEMAN E, et al. Combustor design criteria validation: Volume Ⅱ development testing of two full-scale annular gas turbine combustors[R]. USA-RTL-TR-78-55B(AD-AO-67689), 1979. [16] MONGIA H, SMITH K. An empirical/analytical design methodology for gas turbine combustors[C]//Proceedings of the 14th Joint Propulsion Conference. Las Vegas, US: AIAA, 1978: 978-998. [17] 林志勇,颜应文,李井华,等. 辅助动力装置环形回流燃烧室数值研究[J]. 航空动力学报,2012,27(8): 1726-1733.LIN Zhiyong,YAN Yingwen,LI Jinghua,et al. Numerical study of auxiliary power unit annular backflow combustor[J]. Journal of Aerospace Power,2012,27(8): 1726-1733. (in Chinese) [18] 陈利强,颜应文,徐榕,等. 辅助动力装置全环形燃烧室燃烧性能试验研究[J]. 热能动力工程,2013,28(1): 7-12,105.CHEN Liqiang,YAN Yingwen,XU Rong,et al. Experimental study on combustion performance of full annular combustion chamber of auxiliary power unit[J]. Journal of Engineering for Thermal Energy and Power,2013,28(1): 7-12,105. (in Chinese) [19] 黄夫龙. 辅助动力装置回流燃烧室设计与性能研究[D]. 南京: 南京航空航天大学, 2016.HUANG Fulong. Research on design and performance of auxiliary power unit reverse-flow combustor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese) [20] 常博博,苏三买,刘铁庚,等. 辅助动力装置建模及数值仿真[J]. 航空动力学报,2011,26(9): 2122-2127.CHANG Bobo,SU Sanmai,LIU Tiegeng,et al. Model and numerical simulation of auxiliary power unit[J]. Journal of Aerospace Power,2011,26(9): 2122-2127. (in Chinese) [21] 蔡文祥. 环形燃烧室两相燃烧流场与燃烧性能数值研究[D]. 南京: 南京航空航天大学, 2007.CAI Wenxiang. Research on numerical simulation of two-phase reacting flow field and combustion performance of annular combustors[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2007. (in Chinese) -
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