某型全环燃烧室点火特性试验

丁国玉; 马丹; 高雅; 陶焰明; 刘达兵

doi:10.13224/j.cnki.jasp.20210532

某型全环燃烧室点火特性试验

doi: 10.13224/j.cnki.jasp.20210532

1.
中国航发湖南动力机械研究所，湖南株洲 412002
2.
中国航发南方工业有限公司，湖南株洲 412002

基金项目: 国家科技重大专项（2017-Ⅲ-0007-0032）

详细信息

作者简介:
丁国玉（1985-），男，高级工程师，博士，主要从事航空发动机燃烧室和燃烧理论的研究。E-mail：dgy812@163.com

中图分类号: V231.3
计量
- 文章访问数: 730
- HTML浏览量: 205
- PDF量: 103
- 被引次数: 0
出版历程
- 收稿日期: 2021-09-22
- 网络出版日期: 2023-04-29

Experiment on ignition performance of a full annular combustor

1.
Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China
2.
South Industry Company Limited， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
对某型全环燃烧室进行了模拟地面起动和高空状态下的点火性能试验，研究表明：着火及联焰油气比均随燃烧室进口马赫数的增大而减小；随着模拟点火高度增加，点火变得越来越困难，特别是在试验工况中的低进口马赫数状态下；着火、联焰边界对应的油气比均随换算参考速度的增加而减小，且符合幂函数的函数形式，通过拟合得到着火、联焰边界对应的油气比与换算参考速度之间的函数关系式，经与试验值对比，着火、联焰边界预估值的误差大多分别不超过10%和15%。
- 全环燃烧室 /
- 着火边界油气比 /
- 联焰边界油气比 /
- 点火特性 /
- 换算参考速度
Abstract:
Experiments were conducted to study the ignition performance on a full annular combustor by simulating the ground start and high-altitude ignition parameters. The test results showed that the fuel-air ratio of both the stable flame establishment and the flame propagation from the ignition dome to the unburned dome decreased with the increasing inlet airflow Mach number; ignition became more and more difficult with the increase of simulating ignition height, especially at low inlet Mach number condition; the fuel-air ratio of stable flame establishment limit and the light around limit decreased with the increase of corrected reference velocity, and there was a power function relationship between them; the functional relationship was obtained by fitting; if compared with the test values, the errors of the estimated fuel-air ratio of stable flame establishment limit and light around limit were mostly less than 10% and 15%, respectively.
- full annular combustor /
- fuel-air ratio of stable flame establishment limit /
- fuel-air ratio of the light around limit /
- ignition performance /
- corrected reference velocity

HTML

图 1 燃烧室模型

Figure 1. Combustor model

下载: 全尺寸图片幻灯片

图 2 全环燃烧室试验系统示意图

Figure 2. Experimental system diagram of full annular combustor

下载: 全尺寸图片幻灯片

图 3 进口测点分布示意图

Figure 3. Diagram of inlet measuring points

下载: 全尺寸图片幻灯片

图 4 出口测点分布示意图

Figure 4. Diagram of outlet measuring points

下载: 全尺寸图片幻灯片

图 5 着火边界对应的油气比随进口马赫数的变化

Figure 5. Fuel-air ratio of stable flame establishment limit versus inlet Mach number

下载: 全尺寸图片幻灯片

图 6 联焰边界对应的油气比随进口马赫数的变化

Figure 6. Fuel-air ratio of light around limit versus inlet Mach number

下载: 全尺寸图片幻灯片

图 7 着火/联焰边界对应的油气比随换算参考速度的变化

Figure 7. Fuel-air ratio of stable flame establishment limit/light around limit versus corrected reference velocity

下载: 全尺寸图片幻灯片

图 8 试验与计算着火边界油气比的对比

Figure 8. Comparison between test value and calculation value of fuel-air ratio of stable flame establishment limit

下载: 全尺寸图片幻灯片

图 9 试验与计算联焰边界油气比的对比

Figure 9. Comparison between test value and calculation value of fuel-air ratio of light around limit

下载: 全尺寸图片幻灯片

表 1 主要测试设备

Table 1. Main measurement device

参数名称	测试设备	测量范围	精度
进出口压力	PSI9016	（0.2～1.5）×10⁵ Pa	±0.5%
进口温度	K型热电偶	（−60～100）℃	±1℃
出口温度	B型热电偶	（100～1700）℃	±5℃
燃油流量	流量计	（1～100）g/s	±0.5%
空气流量	质量流量喷嘴	（0.05～2.0）kg/s	±1.0%
燃油温度	K型热电偶	（−60～100）℃	±1℃

下载: 导出CSV

表 2 点火试验状态参数

Table 2. Ignition test parameters

状态名称	进口空气流量/ （kg/s）	进口空气总温/℃	进口空气总压/kPa
模拟地面起动	0.100	室温	室压
模拟地面起动	0.200	室温	室压
模拟4500 m	0.137	−14.3	57.7
模拟4500 m	0.206	−14.3	57.7
模拟6000 m	0.073	−24.0	47.2
	0.112
	0.169
模拟7500 m	0.062	−33.8	38.3
	0.091
	0.137
模拟8500 m	0.118	−40.3	33.1

下载: 导出CSV

参考文献(18)

[1]	LEFEBVRE A H. Gas turbine combustion[M]. New York: Taylor and Francis, 1999.
[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]	READ R J, HOCHGREB S. Relight imaging at low temperature, low pressure conditions[R]. AIAA 2008-0957, 2008.
[4]	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. 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)
[5]	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 performance[J]. Journal of Aerospace Power,2015,30(5): 1092-1098. (in Chinese)
[6]	代威,林宇震,许全宏,等. 径向旋流器气量分配对点火熄火特性的影响[J]. 航空动力学报,2016,31(3): 608-615. DAI Wei,LIN Yuzhen,XU Quanhong,et al. Influence of air split of a radial swirler on ignition and extinction characteristics[J]. Journal of Aerospace Power,2016,31(3): 608-615. (in Chinese)
[7]	杨金虎,刘存喜,刘富强,等. 分级燃烧室预燃级旋流组织对点熄火性能影响的试验研究[J]. 推进技术,2019,40(9): 2050-2059. YANG Jinhu,LIU Cunxi,LIU Fuqiang,et al. Experimental investigation of effects of pilot swirl flow organization on ignition and LBO performance for a staged combustor[J]. Journal of Propulsion Technology,2019,40(9): 2050-2059. (in Chinese)
[8]	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. Influence of the swirl cup flares design on the small combustor ignition performances[J]. Journal of Aerospace Power,2011,26(8): 1708-1712. (in Chinese)
[9]	杨谦,林宇震,代威,等. 主燃孔轴向位置对低压点火性能的影响[J]. 航空动力学报,2015,30(5): 1057-1066. YANG Qian,LIN Yuzhen,DAI Wei,et al. Ignition performance affected by axial position of primary holes at low pressure conditions[J]. Journal of Aerospace Power,2015,30(5): 1057-1066. (in Chinese)
[10]	李继保,刘大响. 局部富油供油扩展燃烧室贫油点火熄火边界研究[J]. 航空动力学报,2003,18(2): 221-224. LI Jibao,LIU Daxiang. A study of local rich fueling design for widening combustor lean ignition and blowout limits[J]. Journal of Aerospace Power,2003,18(2): 221-224. (in Chinese)
[11]	赵明龙,杨志民,林宇震,等. 单头部/扇形/全环燃烧室贫油点火性能换算[J]. 航空动力学报,2017,32(8): 1822-1826. ZHAO Mingling,YANG Zhimin,LIN Yuzhen,et al. Conversion methods for lean ignition performances among single-sector, multi-sector and full annular combustors[J]. Journal of Aerospace Power,2017,32(8): 1822-1826. (in Chinese)
[12]	王高峰,夏一帆,叶沉然,等. 环形燃烧室周向点火机理基础研究进展[J]. 实验流体力学,2019,33(1): 14-28. WANG Gaofeng,XIA Yifan,YE Chenran,et al. Progress on light-round ignition dynamics in annular combustor[J]. Journal of Experiments in Fluid Mechanics,2019,33(1): 14-28. (in Chinese)
[13]	令狐昌鸿,王高峰,钟亮,等. 环形旋流燃烧室模型点火过程的实验[J]. 航空动力学报,2018,33(7): 1767-1778. LINGHU Changhong,WANG Gaofeng,ZHONG Liang,et al. Experiment on ignition process in annular swirling combustor model[J]. Journal of Aerospace Power,2018,33(7): 1767-1778. (in Chinese)
[14]	BOILEAU M,STAFFELBACH G,CUENOT B,et al. LES of ignition sequence in a gas turbine engine[J]. Combustion and Flame,2008,154(1/2): 2-22.
[15]	LACAZE G,RICHARDSON E,POINSOT T. Large eddy simulation of spark ignition in a turbulent methane jet[J]. Combustion and Flame,2009,156(10): 1993-2009. doi: 10.1016/j.combustflame.2009.05.006
[16]	JONES W P,PRASAD V N. LES-PDF simulation of a spark ignited turbulent methane jet[J]. Proceedings of the Combustion Institute,2011,33(1): 1355-1363. doi: 10.1016/j.proci.2010.06.076
[17]	SUBRAMANIAN V,DOMINGO P,VERVISCH L. Large eddy simulation of forced ignition of an annular bluff-body burner[J]. Combustion and Flame,2010,157(3): 579-601. doi: 10.1016/j.combustflame.2009.09.014
[18]	肖为,江立军,陈盛. 燃烧室电火花模型[J]. 航空动力学报,2021,36(1): 25-33. XIAO Wei,JIANG Lijun,CHEN Sheng. Spark ignition model for combustor[J]. Journal of Aerospace Power,2021,36(1): 25-33. (in Chinese)