燃烧室低温燃油火炬式点火性能试验研究

杨珂; 顾烨峰; 杨阳; 汪洋; 唐阳; 颜应文

doi:10.13224/j.cnki.jasp.20250144

燃烧室低温燃油火炬式点火性能试验研究

doi: 10.13224/j.cnki.jasp.20250144

杨珂^{1, 2,},
顾烨峰¹,
杨阳²,
汪洋²,
唐阳²,
颜应文^1,*, ,

1.
南京航空航天大学能源与动力学院，南京 210016
2.
中国航发贵阳发动机设计研究所，贵阳 550081

基金项目: 国家自然科学基金（U2141221）

详细信息

作者简介:
杨珂（1986-），男，硕士生，主要从事航空发动机燃烧室试验研究。E-mail：keinyan@sina.com

通讯作者:
颜应文（1978-），男，教授、博士生导师，博士，主要从事航空发动机燃烧技术研究。E-mail：yanyw@nuaa.edu.cn

中图分类号: V231
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- PDF量: 25
- 被引次数: 0
出版历程
- 收稿日期: 2025-03-25
- 网络出版日期: 2026-06-25

Experimental study on low-temperature torch ignition performance of combustor

Yang Ke^{1, 2
,},
Gu Yefeng¹,
Yang Yang²,
Wang Yang²,
Tang Yang²,
Yan Yingwen^{1,*
, ,}

1.
College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Guiyang Aero Engine Research Institute，Aero Engine Corporation of China，Guiyang 550081，China

摘要

摘要:
针对某型采用火炬式点火的三头部扇形燃烧室，研究了低温燃油条件下的点火性能及其影响因素。设计了低温燃油供油系统，采用高速摄影仪捕捉点火联焰动态过程，试验研究了不同总压损失和点火器引气孔大小对点火特性的影响规律。结果表明：低温燃油条件下，燃烧室点火性能显著下降。工况1与工况3下，起动喷嘴供油质量流量达到9 kg/h便无法成功点火；增大火炬式点火器引气孔面积和提高总压损失系数有助于改善点火性能，拓宽发动机工作包线；−35 ℃低温燃油对远离点火器的头部联焰过程影响较大，显著延长了着火延迟时间。点火完成时长最慢为806 ms，而常温燃油条件下点火完成时长可缩短至433 ms。
- 火炬式点火 /
- 低温燃油 /
- 总压损失 /
- 引气孔 /
- 联焰
Abstract:
This study examined the ignition performance and its influencing factors for a triple-header combustor employing torch ignition under low-temperature fuel conditions. A specialized low-temperature fuel delivery system was designed, and high-speed imaging techniques were utilized to capture the dynamic flame propagation process during ignition. Experimental investigations were conducted to analyze the effects of total pressure loss and air intake orifice size of the igniter on ignition characteristics. The results demonstrated that the ignition performance of the combustor deteriorated significantly under low-temperature fuel conditions. Under condition 1 and condition 3, successful ignition could not be achieved when the fuel supply rate of the starting nozzle reached 9 kg/h. Enlarging the air intake orifice area of the torch igniter and increasing the total pressure loss coefficient were found to enhance the ignition performance and extend the operational envelope of the engine. Furthermore, −35 ℃ low-temperature fuel substantially affected the flame propagation process to sectors distant from the igniter, markedly increasing the ignition delay time. The longest ignition completion time was 806 ms, while under normal-temperature fuel conditions, it could be reduced to 433 ms.
- torch ignition /
- low-temperature fuel /
- total pressure loss /
- ignition vent /
- flame propagation

HTML

图 1 三头部燃烧室

Figure 1. Triple-head combustion chamber

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图 2 火炬式点火器结构示意图

Figure 2. Schematic diagram of torch-type igniter structure

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图 3 试验系统

Figure 3. Test system

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图 4 制冷系统

Figure 4. Refrigeration system

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图 5 点火时序

Figure 5. Ignition sequence

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图 6 点火火舌

Figure 6. Ignition flame tongue

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图 7 工况6联焰过程

Figure 7. Flame connection process in operating condition 6

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图 8 工况9联焰过程

Figure 8. Flame connection process in operating condition 9

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图 9 状态8联焰过程

Figure 9. Flame connection process in operating condition 8

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图 10 壳体出口处横向截面流场

Figure 10. Flow field at the transverse cross-section of the igniter outlet

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图 11 火焰亮度积分曲线

Figure 11. Integrated flame brightness curve

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图 12 联焰动态过程时间

Figure 12. Time of flame connection dynamic process

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表 1 试验状态参数

Table 1. Test state parameters

工况	$ \xi $/%	引气孔径Φ/mm	燃油温度/℃
1	0.6	7	−35
2	0.6	11	−35
3	1	7	−35
4	1	11	−35
5	2	7	−35
6	2	11	−35
7	1	7	26.85
8	1	11	26.85
9	2	11	26.85

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表 2 不同工况燃烧室点火情况

Table 2. Ignition conditions in combustion chambers under different operating conditions

工况	起动喷嘴供油流量/（kg/h）
工况	4	6.5	9
1	√	√	×
2	√	√	√
3	√	√	×
4	√	√	√
5	√	√	√
6	√	√	√
7	√	√	√
8	√	√	√
9	√	√	√

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