掺混结构对脉冲爆震起爆及传播特性影响研究

邵恺元; 王永佳; 张永辉; 黄俊杰; 陈端; 冯再杰; 张启斌; 范玮

doi:10.13224/j.cnki.jasp.20250337

掺混结构对脉冲爆震起爆及传播特性影响研究

doi: 10.13224/j.cnki.jasp.20250337

邵恺元^1,,
王永佳²,
张永辉¹,
黄俊杰³,
陈端¹,
冯再杰¹,
张启斌^{1, 4,*, ,},
范玮^{1, 4}

1.
西北工业大学动力与能源学院，西安 710129
2.
中国航天科技集团有限公司航天推进技术研究院，西安 710100
3.
中国航发湖南动力机械研究所，湖南株洲 412002
4.
西北工业大学轻型涡轮动力国家重点实验室，西安 710129

基金项目: 国家自然科学基金（52176133，52106172）

详细信息

作者简介:
邵恺元（2000-），男，硕士生，主要研究方向为航空发动机燃烧室设计。E-mail：shaokaiyuan@mail.nwpu.edu.cn

通讯作者:
张启斌（1990-），男，副教授，博士，主要研究方向为爆震燃烧与爆震推进。E-mail：zhangqibin@nwpu.edu.cn

中图分类号: V231.2
计量
- 文章访问数: 226
- HTML浏览量: 182
- PDF量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2025-07-16
- 网络出版日期: 2025-10-24

Study on influence of mixing structure on pulse detonation wave initiation and propagation characteristics

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China
2.
China Academy of Aerospace Propulsion，China Aerospace Science and Technology Corporation，Xi’an 710100，China
3.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China
4.
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
为获得冲压模态下吸气式脉冲爆震发动机头部掺混结构对工作特性的影响，以汽油为燃料，空气为氧化剂，通过实验探索了掺混结构对于爆震起爆及传播特性的影响规律，实现了频率为12.5 Hz的稳定爆震，归纳出6种燃烧状态。结果表明：受旋流影响，相较于无旋流结构，有旋流结构对空气来流总压、汽油流量以及点火能量较为敏感，随着点火能量降低，不稳定燃烧持续时间加长，在点火能量下降至3 J时，会导致点火失败，稳定工作当量比范围更窄，但有旋流结构可进一步缩短起爆距离，增加掺混结构的阻塞比可拓宽稳定爆震的当量比范围。
- 吸气式脉冲爆震发动机 /
- 燃烧状态 /
- 爆震波 /
- 点火能量 /
- 当量比
Abstract:
In order to obtain the influences of the mixing structure of air-breathing pulse detonation engine head on the working characteristics in the ramjet mode, gasoline was used as fuel and air was used as oxidizer. The influences of the mixing structure on the detonation initiation and propagation characteristics were explored through experiments. A stable detonation with a frequency of 12.5 Hz was achieved, and six combustion modes were summarized. The results showed that compared with the non-swirl structure, the swirl structure was more sensitive to the total pressure of air flow, gasoline flow and ignition energy. As the ignition energy decreased, the duration of unstable combustion increased. When the ignition energy decreased to 3 J, it may lead to ignition failure and a narrower range of stable equivalence ratio. However, the swirl structure can further shorten the detonation distance, and increasing the blockage ratio of the mixing structure can broaden the equivalence ratio range of stable detonation.
- air-breathing pulse detonation engine /
- combustion mode /
- detonation wave /
- ignition energy /
- equivalence ratio

HTML

图 1 实验系统原理图（单位：mm）

Figure 1. Experimental system diagram （unit：mm）

下载: 全尺寸图片幻灯片

图 2 不同燃烧状态对应的压力波形

Figure 2. Pressure histories corresponding to different combustion modes

下载: 全尺寸图片幻灯片

图 3 无旋流掺混结构的燃烧状态分布图（R_BR=0.36）

Figure 3. Combustion mode of swirlless mixing structure （R_BR=0.36）

下载: 全尺寸图片幻灯片

图 4 旋流掺混结构的燃烧状态分布图（R_BR=0.36）

Figure 4. Combustion mode of swirling mixing structure （R_BR=0.36）

下载: 全尺寸图片幻灯片

图 5 NS-BR0.36中直管传播段的压力波形

Figure 5. Pressure histories in the propagation section of the straight pipe in NS-BR0.36

下载: 全尺寸图片幻灯片

图 6 S-BR0.36中直管传播段的压力波形

Figure 6. Pressure histories in the propagation section of the straight pipe in S-BR0.36

下载: 全尺寸图片幻灯片

图 7 旋流掺混结构的燃烧状态分布图（R_BR =0.61）

Figure 7. Combustion mode of swirling mixing structure（R_BR =0.61）

下载: 全尺寸图片幻灯片

图 8 S-BR0.61中直管传播段压力波形与波速对比

Figure 8. Pressure histories in the propagation section of the straight pipe in S-BR0.61

下载: 全尺寸图片幻灯片

图 9 不同点火能量下S-BR0.61的实验结果

Figure 9. Experimental results of S-BR0.61 under different ignition energies

下载: 全尺寸图片幻灯片

图 10 不同点火能量下NS-BR0.36的实验结果

Figure 10. Experimental results of NS-BR0.36 under different ignition energies

下载: 全尺寸图片幻灯片

参考文献(25)

[1]	ROY G D. Practical pulse detonation engines: how far are they? [C]//Proceedings of the15th International Society for Air Breathing Engines. Bangalore, India: ISABE, 2001: 1170.
[2]	KASAHARA J, HASEGAWA A, NEMOTO T, et al. Performance validation of a single-tube pulse detonation rocket system[J]. Journal of Propulsion and Power, 2009, 25(1): 173-180. doi: 10.2514/1.37924
[3]	KAILASANATH K. Research on pulse detonation combustion systems: a status report: AIAA2009-631 [R]. Orlando, US: AIAA, 2009.
[4]	FAN W. Research progress on pulse detonation rocket engines[C]// Proceedings of International Workshop on Detonation for Propulsion. Pusan, Korea: IWDP, 2011: 14-15.
[5]	HELMAN D, SHREEVE R, EIDELMAN S. Detonation pulse engine: AIAA1986-1683[R]. Huntsville, US: AIAA, 1986.
[6]	严传俊, 何立明, 范玮, 等. 脉冲爆震发动机的研究与发展[J]. 航空动力学报, 2001, 16(3): 212-217. YAN Chuanjun, HE Liming, FAN Wei, et al. Research and development of pulse detonation engines[J]. Journal of Aerospace Power, 2001, 16(3): 212-217. (in Chinese YAN Chuanjun, HE Liming, FAN Wei, et al. Research and development of pulse detonation engines[J]. Journal of Aerospace Power, 2001, 16(3): 212-217. (in Chinese)
[7]	BUSSING T, HINKEY J, KAYE L. Pulse detonation engine preliminary design considerations: AIAA-1994-3220 [R]. Indianapolis, US: AIAA, 1994.
[8]	FALEMPIN F, BOUCHAUD D, DANIAU E. Pulsed detonation engine-towards a tactical missile application: AIAA2000-3473 [R]. Huntsville, US: AIAA, 2000.
[9]	严传俊, 范玮. 脉冲爆震发动机原理及关键技术[M]. 西安: 西北工业大学出版社, 2005. YAN Chuanjun, FAN Wei. Principle and key technology of pulse detonation engine[M]. Xi’an: Northwestern Polytechnical University Press, 2005. (in Chinese YAN Chuanjun, FAN Wei. Principle and key technology of pulse detonation engine[M]. Xi’an: Northwestern Polytechnical University Press, 2005. (in Chinese)
[10]	张群, 范玮. 多管吸气式两相脉冲爆震发动机实验[J]. 航空动力学报, 2012, 27(9): 1935-1938. ZHANG Qun, FAN Wei. Experiment on multi-tube air-breathing two phase pulse detonation engine[J]. Journal of Aerospace Power, 2012, 27(9): 1935-1938. (in Chinese ZHANG Qun, FAN Wei. Experiment on multi-tube air-breathing two phase pulse detonation engine[J]. Journal of Aerospace Power, 2012, 27(9): 1935-1938. (in Chinese)
[11]	袁成, 范玮, 彭畅新, 等. 六管吸气式脉冲爆震发动机试验[J]. 航空动力学报, 2011, 26(9): 1981-1985. YUAN Cheng, FAN Wei, PENG Changxin, et al. Experimental investigation on a six-tube air-breathing pulse detonation engine[J]. Journal of Aerospace Power, 2011, 26(9): 1981-1985. (in Chinese YUAN Cheng, FAN Wei, PENG Changxin, et al. Experimental investigation on a six-tube air-breathing pulse detonation engine[J]. Journal of Aerospace Power, 2011, 26(9): 1981-1985. (in Chinese)
[12]	姜日红, 武晓松, 陈新发, 等. 分流式气动阀流阻及雾化特性研究[J]. 弹箭与制导学报, 2013, 33(3): 91-94, 118. JIANG Rihong, WU Xiaosong, CHEN Xinfa, et al. The research on flow drag and atomization characteristics of shunt aerodynamic valve[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(3): 91-94, 118. (in Chinese JIANG Rihong, WU Xiaosong, CHEN Xinfa, et al. The research on flow drag and atomization characteristics of shunt aerodynamic valve[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(3): 91-94, 118. (in Chinese)
[13]	李海鹏, 何立明, 李天亮, 等. 钝体/阻流孔式气动阀工作机理及流阻特性研究[J]. 航空动力学报, 2008, 23(8): 1480-1485. LI Haipeng, HE Liming, LI Tianliang, et al. Research on mechanism and flow drag character of an aerodynamic valve with blunt block and backflow damping orifices[J]. Journal of Aerospace Power, 2008, 23(8): 1480-1485. (in Chinese LI Haipeng, HE Liming, LI Tianliang, et al. Research on mechanism and flow drag character of an aerodynamic valve with blunt block and backflow damping orifices[J]. Journal of Aerospace Power, 2008, 23(8): 1480-1485. (in Chinese)
[14]	郑殿峰, 杨义勇, 王家骅. 脉冲爆震发动机旋流式气动阀的设计与实验[J]. 航空动力学报, 2010, 25(7): 1471-1477. ZHENG Dianfeng, YANG Yiyong, WANG Jiahua. Design and experimental study on whirl aero-valve for pulse detonation engine[J]. Journal of Aerospace Power, 2010, 25(7): 1471-1477. (in Chinese ZHENG Dianfeng, YANG Yiyong, WANG Jiahua. Design and experimental study on whirl aero-valve for pulse detonation engine[J]. Journal of Aerospace Power, 2010, 25(7): 1471-1477. (in Chinese)
[15]	郑殿峰, 王家骅, 王波, 等. 脉冲爆震发动机气动阀阻力特性[J]. 推进技术, 2004, 25(2): 152-155. ZHENG Dianfeng, WANG Jiahua, WANG Bo, et al. Resistance characteristic of aerovalve of pulse detonation engine[J]. Journal of Propulsion Technology, 2004, 25(2): 152-155. (in Chinese ZHENG Dianfeng, WANG Jiahua, WANG Bo, et al. Resistance characteristic of aerovalve of pulse detonation engine[J]. Journal of Propulsion Technology, 2004, 25(2): 152-155. (in Chinese)
[16]	杨光远. 气动阀式PDE推力性能分析与实验研究[D]. 南京: 南京航空航天大学, 2017. YANG Guangyuan. Analysis and experimental investigation on the thrust performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017. (in Chinese YANG Guangyuan. Analysis and experimental investigation on the thrust performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017. (in Chinese)
[17]	宫继双. 提高气动阀式脉冲爆震发动机性能的技术研究[D]. 南京: 南京航空航天大学, 2012. GONG Jishuang. Investigation on improving performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese GONG Jishuang. Investigation on improving performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)
[18]	熊姹, 王治武, 严传俊, 等. 脉冲爆震发动机头部雾化、掺混实验研究[J]. 西北工业大学学报, 2005, 23(6): 742-745. XIONG Cha, WANG Zhiwu, YAN Chuanjun, et al. Improving atomization and mixture in pulsed detonation engine (PDE)[J]. Journal of Northwestern Polytechnical University, 2005, 23(6): 742-745. (in Chinese XIONG Cha, WANG Zhiwu, YAN Chuanjun, et al. Improving atomization and mixture in pulsed detonation engine (PDE)[J]. Journal of Northwestern Polytechnical University, 2005, 23(6): 742-745. (in Chinese)
[19]	QIU Hua, XIONG Cha, YAN Chuanjun, et al. Effect of aerodynamic valve on backflow in pulsed detonation tube[J]. Aerospace Science and Technology, 2013, 25(1): 1-15. doi: 10.1016/j.ast.2011.12.003
[20]	MA Hu, WU Xiaosong, WANG Dong, et al. Experimental investigation of multi-cycle pulse detonation engine at different air inlet systems[J]. Proceedings of the Institution of Mechanical Engineers: Part G Journal of Aerospace Engineering, 2014, 228(12): 2207-2214. doi: 10.1177/0954410013514029
[21]	郑殿峰, 张会强, 王家骅. 气动阀型式对脉冲爆震发动机爆震特性的影响[J]. 南京航空航天大学学报, 2009, 41(2): 187-191. ZHENG Dianfeng, ZHANG Huiqiang, WANG Jiahua. Effects of aerovalve structure on performance of PDE[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2009, 41(2): 187-191. (in Chinese ZHENG Dianfeng, ZHANG Huiqiang, WANG Jiahua. Effects of aerovalve structure on performance of PDE[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2009, 41(2): 187-191. (in Chinese)
[22]	谭汶昊, 郑龙席, 黄康, 等. U型脉冲爆震燃烧室的点火起爆工作特性试验研究[J]. 推进技术, 2022, 43(1): 200742. TAN Wenhao, ZHENG Longxi, HUANG Kang, et al. Experimental investigation on ignition and detonation characteristics of U-bend pulse detonation combustor[J]. Journal of Propulsion Technology, 2022, 43(1): 200742. (in Chinese TAN Wenhao, ZHENG Longxi, HUANG Kang, et al. Experimental investigation on ignition and detonation characteristics of U-bend pulse detonation combustor[J]. Journal of Propulsion Technology, 2022, 43(1): 200742. (in Chinese)
[23]	谭汶昊, 郑龙席, 卢杰, 等. 高温来流下U型脉冲爆震燃烧室燃烧特性试验[J]. 航空动力学报, 2022, 37(3): 502-510. TAN Wenhao, ZHENG Longxi, LU Jie, et al. Experiment on combustion characteristics of U-bend pulse detonation combustor under high temperature inlet stream[J]. Journal of Aerospace Power, 2022, 37(3): 502-510. (in Chinese TAN Wenhao, ZHENG Longxi, LU Jie, et al. Experiment on combustion characteristics of U-bend pulse detonation combustor under high temperature inlet stream[J]. Journal of Aerospace Power, 2022, 37(3): 502-510. (in Chinese)
[24]	赵炜, 韩启祥, 王家骅, 等. 热射流点火对多循环爆震管内火焰传播特性的影响[J]. 推进技术, 2015, 36(12): 1846-1851. ZHAO Wei, HAN Qixiang, WANG Jiahua, et al. Effects of hot jet ignition on flame propagation characteristics in multi-cycle detonation tube[J]. Journal of Propulsion Technology, 2015, 36(12): 1846-1851. (in Chinese ZHAO Wei, HAN Qixiang, WANG Jiahua, et al. Effects of hot jet ignition on flame propagation characteristics in multi-cycle detonation tube[J]. Journal of Propulsion Technology, 2015, 36(12): 1846-1851. (in Chinese)
[25]	QIU Hua, SU Zheng, XIONG Cha. Experimental investigation on multi-cycle two-phase spiral pulse detonation tube of two configurations[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019, 233(11): 4166-4175. doi: 10.1177/0954410018817455