双级轴向旋流器设计参数对燃烧室点火性能影响规律

王金铎; 惠鑫; 武济泓; 蒋尧; 林宇震

doi:10.13224/j.cnki.jasp.20220296

双级轴向旋流器设计参数对燃烧室点火性能影响规律

doi: 10.13224/j.cnki.jasp.20220296

王金铎¹,
惠鑫^1,*, ,,
武济泓²,
蒋尧³,
林宇震¹

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
中国航空工业集团有限公司西安飞机工业集团股份有限公司，西安 710089
3.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 中国航空发动机集团产学研合作项目（HFZL2021CXY003）

详细信息

作者简介:
王金铎（1995-），男，博士生，主要从事航空燃料燃烧特性与燃烧室性能研究

通讯作者:
惠鑫（1982-），男，副教授、博士生导师，博士，主要从事航空能源与动力技术研究。E-mail：huixin@buaa.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2022-05-01
- 网络出版日期: 2022-09-15

Effects of design parameters of two-stage axial swirler on combustor ignition performance

1.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
2.
Xi’an Aircraft Industry Group Company，Limited， Aviation Industry Corporation of China，Limited，Xi’an 710089，China
3.
Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
为有效提升航空发动机燃烧室点火性能，以双级轴向旋流器为研究对象，采用三种气动结构参数为设计变量，开展了旋流器优化设计与燃烧室点火性能研究。研究通过试验测量了不同旋流器匹配的单头部燃烧室地面点火与模拟高空点火油气比，获得了旋流器气动结构参数与燃烧室点火性能之间的关联。研究结果表明：在保持总有效面积和内旋流数不变条件下，外旋流数从1.77增加至2.15时，燃烧室点火性能呈现先降低后升高的趋势，较小外旋流数点火特性更佳；内外有效面积比对高空低压工况燃烧室点火性能影响显著，在比值为3∶7时点火特性最佳。在保持其他结构参数不变条件下，文氏管喉道半径对燃烧室高空点火性能影响显著，喉道半径为8 mm时具有较好点火特性。
- 燃烧室点火性能 /
- 双级轴向旋流器 /
- 旋流强度 /
- 有效面积 /
- 文氏管喉道
Abstract:
To improve the ignition performance of the aero-engine combustor, different configurations of two-stage axial swirlers were designed based on the swirler design parameters. Ground and high-altitude ignition tests were carried out to obtain the ignition fuel-air-ratios for a model combustor equipped with the designed swirlers. The effects of outer swirl number, the air split ratio between the inner and outer swirlers, and Venturi throat size on combustor ignition performance were analyzed. The results showed that under the same total air flow rate and inner swirl number, when the outer swirl number increased from 1.77 to 2.15, the combustor ignition performance first decreased and then increased, and the ignition characteristic was better when the outer swirl number was smaller. The inner and outer swirler flow ratios had a significant impact on the combustor ignition performance under high altitude and low pressure conditions, and the ignition characteristic was the best when the ratio was 3∶7. If other structural parameters were kept unchanged, the Venturi throat radius had a significant impact on the high altitude ignition performance of the combustor, and it had good ignition characteristics when the throat radius was 8 mm.
- combustor ignition performance /
- two-stage axial swirlers /
- swirl intensity /
- effective area /
- Venturi throat

HTML

图 1 双级轴向旋流器

Figure 1. Two-stage axial swirlers

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图 2 常压和高空点火试验系统

Figure 2. Ground and high-altitude ignition test system

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图 3 点火过程

Figure 3. Processes of ignition

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图 4 典型工况点火细节图

Figure 4. Ignition details under typical working conditions

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图 5 1#, 2#, 3#旋流器在不同进气压力下点火边界

Figure 5. Ignition boundaries of swirlers 1#, 2#, 3# under different inlet pressures

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图 6 1#, 2#, 3#旋流器在相同进气压力下点火边界

Figure 6. Ignition boundaries of swirlers 1#, 2#, 3# under same inlet pressure

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图 7 #2, #4, #5旋流器在不同进气压力下点火边界

Figure 7. Ignition boundaries of swirlers #2, #4, #5 under different inlet pressures

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图 8 #2, #4, #5旋流器在相同进气压力下点火边界

Figure 8. Ignition boundaries of swirlers #2, #4, #5 under same inlet pressure

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图 9 2#, 6#, 7#旋流器在不同进气压力下点火边界

Figure 9. Ignition boundaries of swirlers 2#, 6#, 7# under different inlet pressures

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图 10 2#, 6#, 7#旋流器在相同进气压力下点火边界

Figure 10. Ignition boundaries of swirlers 2#, 6#, 7# under same inlet pressure

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表 1 双级轴向旋流器设计方案

Table 1. Configurations of two-stage axial swirlers

系列	方案	外旋流数 S_o	内外旋流器有效面积比A_cd1∶A_cd2	喉道半径 r/mm
一	1#	1.77	5∶5	8
	2#	1.97	5∶5	8
	3#	2.15	5∶5	8
	4#	1.81	3∶7	8
二	5#	1.97	4∶6	8
	2#	1.97	5∶5	8
	6#	1.92	9∶10	7
三	2#	1.97	5∶5	8
	7#	1.90	11∶10	9

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表 2 测量参数与精度

Table 2. Measurement parameters and accuracy

测量参数	精度
p₃/Pa	±0.2%
p₄/Pa	±0.2%
T₃/K	±1
$ {\dot m_{\text{a}}} $ /（g/s）	±0.5%
$ {\dot m_{\text{f}}} $/（g/s）	±0.2%

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表 3 试验工况

Table 3. Test conditions

工况	p₃/kPa	（Δp_3-4/p₃）/%	T₃/K
常压	101	1～5	293
高空	80
	55
	35

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参考文献(18)

[1]	方昌德. 世界航空发动机手册[M]. 北京:航空工业出版社,1996.
[2]	LEFEBVRE A H. Gas turbine combustion[M]. New York, US: Hemisphere Publishing Corporation,1983.
[3]	黄勇. 燃烧与燃烧室[M]. 北京:北京航空航天大学出版社,2009.
[4]	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.
[5]	MONGIA H C. Perspective of combustion modeling for gas turbine combustor[R]. AIAA-2004-0156,2004.
[6]	彭云晖,林宇震,许全宏,等. 双旋流空气雾化喷嘴喷雾、流动和燃烧性能[J]. 航空学报,2008,29(1): 1-14. doi: 10.3321/j.issn:1000-6893.2008.01.001 PENG Yunhui,LIN Yuzhen,XU Quanhong,et al. Atomization,aerodynamics and combustion performance of swirl cup[J]. Acta Aeronautica et Astronautica Sinica,2008,29(1): 1-14. (in Chinese) doi: 10.3321/j.issn:1000-6893.2008.01.001
[7]	高政旺,谭建国. 双级轴向旋流器内外叶片角对燃烧室回流区影响的数值研究[R]. 广东深圳: 第十一届全国流体力学学术会议,2020.
[8]	于博文,张弛,杨谦,等. 一级旋流强度对双旋流杯下游油气分布的影响[J]. 推进技术,2014,35(11): 1482-1487. YU Bowen,ZHANG Chi,YANG Qian,et al. Effects of primary swirl intensity on flow and fuel distribution downstream a dual-swirl cup[J]. Journal of Propulsion Technology,2014,35(11): 1482-1487. (in Chinese)
[9]	汪玉明,王志凯,江立军,等. 文氏管出口张角对旋流杯流动不稳定性的影响[J]. 推进技术,2022,43(1): 195-204. WANG Yuming,WANG Zhikai,JIANG Lijun,et al. Effects of venturi divergence angle on flow instability of swirl cup[J]. Journal of Propulsion Technology,2022,43(1): 195-204. (in Chinese)
[10]	王志凯,陈盛,刘冉,等. 双级轴向旋流杯气量比对雾化性能影响的试验[J]. 航空动力学报,2019,34(12): 2656-2662. WANG Zhikai,CHEN Sheng,LIU Ran,et al. Experiment on effects of airflow ratio on spray characteristics of dual-axial swirl cup[J]. Journal of Aerospace Power,2019,34(12): 2656-2662. (in Chinese)
[11]	谢法,黄勇,苗辉,等. 气量分配对双轴向旋流器燃烧室贫熄性能影响[J]. 北京航空航天大学学报,2011,37(11): 1456-1460. XIE Fa,HUANG Yong,MIAO Hui,et al. Effects of airflow split and primary holes arrangement on lean blowout limits of combustor with dual-axial swirlers[J]. Journal of Beijing University of Aeronautics and Astronautics,2011,37(11): 1456-1460. (in Chinese)
[12]	张弛,田兴鹏,林宇震,等. 旋流杯文氏管长度对积碳的影响研究[J]. 推进技术,2015,36(12): 1833-1838. ZHANG Chi,TIAN Xingpeng,LIN Yuzhen,et al. Effects of venturi length of swirl cup on carbon deposition[J]. Journal of Propulsion Technology,2015,36(12): 1833-1838. (in Chinese)
[13]	程明,林宏军,李锋. 旋流杯设计参数对燃烧性能的影响[J]. 航空动力学报,2014,29(10): 2355-2361. CHENG Ming,LIN Hongjun,LI Feng. Effect of swirl cup design parameters on combustion performance[J]. Journal of Aerospace Power,2014,29(10): 2355-2361. (in Chinese)
[14]	刘桂桂,林宇震,胡好生,等. 旋流杯一级旋流数变化对点火性能的影响[J]. 北京航空航天大学学报,2015,41(6): 1117-1121. doi: 10.13700/j.bh.1001-5965.2014.0408 LIU Guigui,LIN Yuzhen,HU Haosheng,et al. Effect of swirl cup's primary swirl number on ignition performance[J]. Journal of Beijing University of Aeronautics and Astronautics,2015,41(6): 1117-1121. (in Chinese) doi: 10.13700/j.bh.1001-5965.2014.0408
[15]	刘冉,陈盛,王志凯,等. 双级轴向涡流器气量分配对燃烧室点火特性的影响[J]. 推进技术,2022,43(8): 253-260. LIU Ran,CHEN Sheng,WANG Zhikai,et al. Effects of dual axial swirler airflow split on combustor ignition characteristics[J]. Journal of Propulsion Technology,2022,43(8): 253-260. (in Chinese)
[16]	罗国良,宋双文,胡好生,等. 旋流杯空气雾化喷嘴套筒出口形状对小型燃烧室点火性能的影响[J]. 航空动力学报,2011,26(8): 1708-1712. LUO Guoliang,SONG Shuangwen,HU Haosheng,et al. Influences of the swirl cup flares design on the small combustor ignition performances[J]. Journal of Aerospace Power,2011,26(8): 1708-1712. (in Chinese)
[17]	代威,林宇震,张弛. 第2级径向旋流器旋流数对燃烧室点火和贫油熄火性能的影响[J]. 航空动力学报,2015,30(5): 1092-1098. DAI Wei,LIN Yuzhen,ZHANG Chi. Effects of swirl number of second stage radial swirler on combustor ignition and lean blow-out performances[J]. Journal of Aerospace Power,2015,30(5): 1092-1098. (in Chinese)
[18]	赵乾鹏,杨金虎,刘存喜,等. 多级旋流空气雾化喷嘴高空气动雾化场的数值研究[J]. 航空动力学报,2021,36(12): 2555-2567. ZHAO Qianpeng,YANG Jinhu,LIU Cunxi,et al. Numerical investigation of high altitude aerodynamic and spray fields for multi-swirl airblast atomizer[J]. Journal of Aerospace Power,2021,36(12): 2555-2567. (in Chinese)