亚临界状态航空煤油的旋转爆震波传播特性实验研究

徐广川; 陈铮; 王晓昆; 孟博威; 马虎

doi:10.13224/j.cnki.jasp.20240265

亚临界状态航空煤油的旋转爆震波传播特性实验研究

doi: 10.13224/j.cnki.jasp.20240265

徐广川^1,,
陈铮²,
王晓昆¹,
孟博威¹,
马虎^1,*, ,

1.
南京理工大学机械工程学院特种动力技术教育部重点实验室，南京 210094
2.
上海机电工程研究所，上海 201109

基金项目: 国家自然科学基金（12072163，52106161）

详细信息

作者简介:
徐广川（1999-），男，博士生，研究领域为旋转爆震推进技术。E-mail：3044998769@qq.com

通讯作者:
马虎（1986-），男，教授、博士生导师，博士，主要从事旋转爆震推进技术研究。E-mail：mahuokok@163.com

中图分类号: V231
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出版历程
- 收稿日期: 2024-04-28
- 网络出版日期: 2025-09-01

Experimental study on rotating detonation wave propagation characteristics of subcritical aviation kerosene

1.
Key Laboratory of Special Engine Technology，Ministry of Education，School of Mechanical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China
2.
Shanghai Electromechanical Engineering Institute，Shanghai 201109，China

摘要

摘要:
为探究亚临界状态下航空煤油与来流空气掺混起爆后的爆震波传播特性，将常温航空煤油加温加压至亚临界状态，分别开展不同来流温度以及燃烧室宽度条件下的旋转爆震燃烧特性实验研究，分析了旋转爆震波起爆与传播的影响因素。实验结果表明：亚临界航空煤油起爆过程分为点火、爆燃转爆震以及爆震波持续稳定传播3个阶段；来流温度在300～700 K范围内，提高来流空气总温能够改善亚临界航空煤油的起爆特性，当来流空气总温由500 K提升至700 K，爆震波起爆时间可从30 ms缩短至16 ms；旋转爆震燃烧室的宽度可影响爆震波的传播稳定性，外径相同时，相同工况下的50 mm宽环形燃烧室只能形成零星爆震波，而空桶燃烧室可以实现稳定的单波爆震燃烧。
- 爆震特性 /
- 传播模态 /
- 空桶燃烧室 /
- 亚临界航空煤油 /
- 来流温度
Abstract:
In order to explore the rotating detonation wave propagation characteristics of aviation kerosene mixed with incoming air in the subcritical state, the ambient aviation kerosene was heated and pressurized to the subcritical state, an experimental study of the combustion characteristics of the rotating detonation under different incoming flow temperatures and combustion chamber widths was carried out, and the influencing factors of the initiation and propagation of the rotating detonation wave were analyzed. The experimental results showed that the initiation process of subcritical aviation kerosene was divided into three stages: ignition, deflagration to detonation and sustained and stable detonation wave propagation. When the total incoming flow temperature ranged from 300 K to 700 K, the detonation characteristics of subcritical aviation kerosene can be improved by increasing the total incoming flow temperature. When the total incoming flow temperature increased from 500 K to 700 K, the detonation time can be shortened from 30 ms to 16 ms. The rotating detonation chamber width can effectively influence the propagation stability of the detonation wave. In case of the same combustion chamber outer diameter, the 50 mm wide annular combustion chamber under the same working condition can only form sporadic detonation waves, while the hollow combustion chamber can realize stable single-wave detonation combustion.
- detonation characteristics /
- propagation mode /
- hollow combustor /
- subcritical aviation kerosene /
- incoming flow temperature

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图 1 实验系统组成示意图

Figure 1. Experimental system planar schematic

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图 2 实验加热装置

Figure 2. Experimental heating device

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图 3 爆震燃烧室结构

Figure 3. Detonation combustion chamber structure

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图 4 径向方向传感器安装位置示意图

Figure 4. Radial direction sensor installation position diagram

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图 5 轴向方向传感器安装位置示意图

Figure 5. Axial direction sensor installation position diagram

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图 6 传感器安装实物图

Figure 6. Sensor installation diagram

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图 7 实验控制时序图

Figure 7. Experiment control time sequence diagram

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图 8 压力信号p₁

Figure 8. Pressure signal p₁

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图 9 离子探针信号I₁和I₂

Figure 9. Ion probe signal I₁ and I₂

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图 10 起爆阶段和传播阶段的压力信号

Figure 10. Pressure signals in deflagration to detonation stage and detonation stable propagation stage

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图 11 离子探针I₂信号

Figure 11. Ion probe signal I₂

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图 12 发动机工作实况

Figure 12. Engine operating condition

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图 13 实验过程各传感器压力曲线

Figure 13. Pressure curve of the sensors during the experiment

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图 14 滤波后的p₁压力信号

Figure 14. Pressure signals p₁ after filtering

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图 15 p₁压力信号局部放大图

Figure 15. Local magnification of pressure signal p₁

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图 16 快速傅里叶变换分析

Figure 16. Fast fourier transform

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图 17 爆震波起爆过程压力信号

Figure 17. Pressure signal of detonation wave during initiation

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图 18 来流空气总温为700 K的p₁压力信号及其局部放大图

Figure 18. Pressure signal p₁ and local magnification diagram at inlet total temperature of 700 K

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图 19 起爆阶段压力信号及离子探针信号I₂

Figure 19. Pressure signal of detonation wave during initiation and ion probe signal I₂

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图 20 滤波后p₁高频压力信号及局部放大图

Figure 20. High frequency pressure signal p₁ and local magnification diagram after filtering

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图 21 离子探针信号I₁和I₂

Figure 21. Ion probe signal I₁ and I₂

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图 22 燃烧室压力信号p_c

Figure 22. Pressure signal p_c of combustion chamber

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表 1 实验工况表

Table 1. Experimental conditions

工况	空气质量流量/ （g/s）	燃油质量流量/ （g/s）	空气总温/K	煤油温度/K	煤油压力/ MPa	当量比（ER）	燃烧室宽度/mm
#1	1500	90	300	573.15	3	1	100
#2	1500	90	500	573.15	3	1	100
#3	1500	90	600	573.15	3	1	100
#4	1500	90	700	573.15	3	1	100
#5	1500	90	600	573.15	3	1	50

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