马赫数4下氢气自燃辅助乙烯点火实验研究

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1628-1635.

马赫数4下氢气自燃辅助乙烯点火实验研究

张弯洲^1,2,乐嘉陵¹,杨顺华¹,程文明²,邓维鑫^1,2

中国空气动力研究与发展中心吸气式高超声速技术研究中心,四川绵阳 621000;中国空气动力研究与发展中心吸气式高超声速技术研究中心,四川绵阳 621000;中国空气动力研究与发展中心吸气式高超声速技术研究中心,四川绵阳 621000;西南交通大学机械工程学院,四川成都 610031;中国空气动力研究与发展中心吸气式高超声速技术研究中心,四川绵阳 621000

发布日期:2021-08-15
作者简介:张弯洲(1984—),男,博士生,研究领域为超燃发动机。E-mail:zwz8410@gmail.com
基金资助:
自然科学青年科学基金(10902109)。

Experimental Research on Ethylene Ignition with Hydrogen Self-Ignition Assistant at Mach 4

Airbreathing Hypersonics Research Center, China Aerodynamics Research and Development Center, Mianyang 621000, China;Airbreathing Hypersonics Research Center, China Aerodynamics Research and Development Center, Mianyang 621000, China;Airbreathing Hypersonics Research Center, China Aerodynamics Research and Development Center, Mianyang 621000, China;School of Mechanical Engineering, Southwest Jiaotong University,Chengdu 610031, China;Airbreathing Hypersonics Research Center, China Aerodynamics Research and Development Center, Mianyang 621000, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究氢气自燃辅助乙烯点火的具体点火参数和点火性能,在直连式脉冲燃烧风洞设备上进行了模拟飞行马赫数4条件下的超燃发动机乙烯点火试验,试验来流的总温935K,总压0.8MPa,隔离段入口马赫数2.1。试验利用不同质量流量的引导氢气自燃辅助点火,成功实现了乙烯燃料的点火和稳定燃烧。通过流场显示和壁面压力测量发现:(1)能够成功点火的引导氢气流量范围为 0.43~12.61g/s,相当于当量比0.005~0.142；(2)0.43g/s流量氢气注入燃烧室后10ms以内被点燃,乙烯燃料注入后经过了约20ms才被点燃,点火的主要位置为凹槽内；(3)6.68g/s的氢气注入燃烧室后20ms才被点燃,乙烯燃料注入后约8ms即被点燃,点火的主要位置为凹槽下游和凹槽出口位置；(4)点火试验中火焰能够在凹槽内和剪切层内向上游逆传；(5)凹槽下游和下壁面的燃烧,是促进凹槽内燃烧、提升燃烧室压力和引起燃烧室压力震荡的主要原因。 

关键词: 超燃冲压发动机;直连式脉冲燃烧风洞;点火试验;火焰传播 

Abstract: Experiments on scramjet combustor ignition were performed on pulse directly-connected combustion facility in the inflow which simulated the flight Mach 4with the total temperature of 935K, total pressure of 0.8MPa and the inflow Mach number of 2.1to confirm the detailed ignition parameters and performance. Pilot hydrogen at various mass flow rate was employed to achieve ethylene ignition and stable combustion. Results of pressure measurement and high speed imaging indicate that:(1) For reliable ignition the mass flow rate of hydrogen range should be from 0.43g/s to 6.68g/s, the equivalence ratio range is from 0.005to 0.142.(2) Hydrogen at 0.43g/s is self-ignited 10ms after injected, and ethylene is ignited 20ms after injected, the main ignition location is in the cavity. (3) Hydrogen at 6.68g/s is self-ignited 20ms after injected and ethylene is ignited 8ms after injected, the main ignition region is located at the exit and downstream of the cavity. (4) Flame could propagate upstream in the shear layer and in cavity. (5) Combustion downstream the cavity is the main cause of promoting combustion in cavity, improving combustor pressure and pressure oscillation.

Key words: Scramjet; Pulse directly-connected combustion facility;Ignition experiment;Flame propagation

张弯洲,乐嘉陵,杨顺华,程文明,邓维鑫. 马赫数4下氢气自燃辅助乙烯点火实验研究[J]. 推进技术, 2013, 34(12): 1628-1635.

ZHANG Wan-zhou^1,2, LE Jia-ling¹, YANG Shun-hua¹, CHENG Wen-ming²,DENG Wei-xin^1,2. Experimental Research on Ethylene Ignition with Hydrogen Self-Ignition Assistant at Mach 4[J]. Journal of Propulsion Technology, 2013, 34(12): 1628-1635.

参考文献

[1] Chadwick C Rasmussen, James F Driscoll, Jeffrey M Donbar,et al.Stability Limits of Cavity-Stabilized Flames in Supersonic Flow [J].Proceedings of the Combustion Institute,2005,0:2825-2833.
[2] Junya Watanabe, Naoyuki Abe, Kenichi Takita.Effect of a Rearward-Facing Step on Plasma Ignition in Supersonic Flow [J].Journal of Spacecraft and Rockets,2009,6(3).
[3] Aleksandrov A, Bychkov V, Chernikov V, et al.Arc Discharge as a Means for Ignition and Combustion of Propane-Air Mixture Supersonic Flow [R].AIAA 2006-1462.
[4] Adela Ben-Yakar,Ronald K Hanson.Cavity Flame-Holder for Ignition and Flame Stabilization in Scramjet:An Overview[J].Journal of Propulsion and Power,2001,7(4).
[5] 张弯洲,乐嘉陵,杨顺华,等.超燃发动机混合效率评估方法探讨 [J].航空动力学报, 2012,7(9).
[6] Lin K C, Kendedy P J,Jackson T A.Penetration Heights of Liquid jets in High-speed Cross-flows [R].AIAA 2002-0873.
[7] CORIN SEGAL.The Scramjet Engine:Processes and Characteristics [M].New York:Cambridge University Press, 2009.
[8] Kuo-Cheng Lin, Chung-Jen Tam, Isaac Boxx,et al.Flame Characteristics and Fuel Entrainment Inside a Cavity Flame Holder in a Scramjet Combustor [R].AIAA 2007-5381.
[9] Vigor Yang, Jian Li, Jeong Yeol Choi, et al.Ignition Transient in an Ethylene Fueled Scramjet Engine with Air Throttling Part I:Non-Reacting Flow Development and Mixing [R].AIAA 2010-409.
[10] Vigor Yang, Jian Li, Jeong Yeol Choi, et al.Ignition Transient in an Ethylene Fueled Scramjet Engine with Air Throttling Part II:Ignition and Flame Development [R].AIAA 2010-410.
[11] 李大鹏,丁猛,梁剑寒,等.Ma=4液体碳氢燃料超燃冲压发动机点火试验[J].推进技术,2009,0(4):385-389.(LI Da-peng, DING Meng, LIANG Jian-han, et al.Ignition Experimental for Liquid Hydrocarbon Fueled Scram Jet with Simulated Flight Mach 4[J].Journal of Propulsion Technology, 2009,0(4):385-389.)
[12] 孙英英,韩肇元, 司徒明, 等.高温富油燃气作引导火焰的煤油超燃研究[J].推进技术,2001,2(2):157-161.(SUN Ying-ying, HAN Zhao-yuan, SITU Ming, et al.Investigation on Supersonic Combustion of Kerosene using Fuel-Rich Hot Gas as Pilot Flame[J].Journal of Propulsion Technology, 2001,2(2):157-161.)
[13] Mathur T, Lin K C, Kennedy P.Liquid JP-7Com-bustion in a Scramjet Combustor[R].AIAA 2000-3581.
[14] Wang Dian, Song Wenyan, Li Jianping,et al.Investigation of Hydrocarbon-Fuel ignition and Combustion in Scramjet Combustor [J].Journal of Solid Rocket Technology, 2008,1(5).
[15] Mathur T, Streby G,Gruber M.Supersonic Combustion Experiments With a Cavity-Based Fuel Injector [R].AIAA 99-2102.