超声速状态下正癸烷和RP3的稳焰特性研究

推进技术 ›› 2015, Vol. 36 ›› Issue (5): 780-788.

超声速状态下正癸烷和RP3的稳焰特性研究

吴　显,林宇震,刘　伟,王建臣

北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点试验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点试验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点试验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点试验室，北京 100191

发布日期:2021-08-15
作者简介:吴　显(1990—)，男，硕士生，研究领域为超声速燃烧。

Flame Stabilization Characteristics of n-Decane and RP3

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 通过直连蓄热式试验台，研究了正癸烷和RP3航空煤油两种碳氢燃料在超燃燃烧室中的稳焰特性。燃烧室采用双凹腔构型作为稳焰结构，进口总温1000~1150K，进口马赫数2.03，分别采用纯液态喷嘴和气泡雾化喷嘴进行燃料喷射。研究结果表明:在所有试验的总温范围内，正癸烷的稳焰性能比RP3略强，另外，两种燃料在纯液态喷射条件下不易实现稳焰，使用气泡雾化喷嘴能有效提高燃料的稳焰性能。文章建立了一个简单的理论模型，以“驻留时间≥反应延迟时间”作为实现稳焰的判据，计算出各试验工况下的驻留时间与反应延迟时间，发现二者均在1ms量级，计算结果与试验结果吻合较好。最后，根据两种燃料的热物性参数，计算了相同工况下二者的液滴平均直径SMD和蒸发常数，发现SMD在10μm量级，正癸烷的雾化和蒸发特性均略优于RP3，因此从燃料热物性角度说明了正癸烷的超燃稳焰性能略优于RP3的原因。

关键词: 超声速燃烧；碳氢燃料；稳焰；理论模型分析

Abstract: The supersonic flame stabilization characteristics of n-decane and aviation kerosene (RP3) in a model scramjet combustor were experimentally investigated through the direct-connect supersonic combustion facility with regenerative storage air heater. Two serial cavities were chosen as the flameholders. Total temperature of a Mach 2.03 supersonic inflow ranged from 1000K to 1150K. Pure-liquid injector and aerated-liquid injector were adopted in experiments. The experimental results show that compared to RP3，n-decane provides slightly better characteristics of flame-holding under the conditions of experiments. Furthermore，it is difficult for pure-liquid fuel to achieve flameholding，the aerated-liquid injector can efficiently improve the flame stabilization characteristics. Applying the flameholding criterion residence time≥reaction delay time，a simple theoretical model was established by calculating the residence time and the reaction delay time of each condition. The results show that the order of two characteristic times is 1ms.And the analysis results are agreeable to the experimental ones. SMD and evaporation constant of n-decane and RP3 under the same conditions were calculated based on thermal physical parameters of the two kinds of fuels. The calculation results show that the order of SMD is 10μm，and n-decane provides slightly better atomization and evaporation characteristics which explain the reason why n-decane provides slightly better supersonic flame stabilization characteristics from the point of thermal physical parameters of fuels.

Key words: Supersonic combustion；Hydrocarbon fuels；Flame stabilization；Theoretical model analysis

吴　显,林宇震,刘　伟,王建臣. 超声速状态下正癸烷和RP3的稳焰特性研究[J]. 推进技术, 2015, 36(5): 780-788.

WU Xian,LIN Yu-zhen,LIU Wei,WANG Jian-chen. Flame Stabilization Characteristics of n-Decane and RP3[J]. Journal of Propulsion Technology, 2015, 36(5): 780-788.

参考文献

[1] Murthy S N B, Curran E T. High-Speed Flight Propulsion Systems[J]. Progress in Astronautics and Aeronautics, 1991, 137: 124-158.
[2] Curran E T. Scramjet Engines: The first Forty Years[J]. Journal of Propulsion and Power, 2001, 17(6): 1138-1148.
[3] Tetlow M R, Doolan C J. Comparison of Hydrogen and Hydrocarbon-Fueled Scramjet Engines for Orbital Insertion[J]. Journal of Spacecraft and Rockets, 2007, 44: 365-373.
[4] Adela Ben-Yakar, Ronald K Hanson. Cavity Flame-Holders for Ignition and Flame Stablization in Scramjets: An Overview[J].Journal of Propulsion and Power, 2001, 17: 869-877.
[5] Lin K C, Kennedy P J, Jackson T A. Spray Penetration Heights of Angled-Injected Aerated-Liquid Jets in Supersonic Crossflow[R]. AIAA 2000-0194.
[6] Lin K C, Kennedy P J, Jackson T A. Structure of Aerated-Liquid Jets in High-Speed Crossflow[R]. AIAA 2002-3187.
[7] Yu G, Li J G, Yang S R, et al. Investigation of Liquid Hydrocabon Combustion in Supersonic Flow Using Effervescent Atomization[R]. AIAA 2002-4279.
[8] Mitsuhiro Tsue, Osamu Imamura, Shunsuke Suzuki, et al. Effects of Fuel Properties on Self-Ignition and Flame-Holding Performances in Scram Jet Combustor for n-Alkane Fuels [J]. Proceedings of the Combustion Institute, 2011, 33(2): 2391-2398.
[9] 肖保国, 杨顺华, 赵慧勇, 等. RP-3航空煤油燃烧的详细和简化化学动力学模型[J]. 航空动力学报, 2010, 25(9): 1948-1955.
[10] 姚通, 钟北京. 正癸烷着火及燃烧的化学动力学模型[J]. 物理化学学报, 2013, 29(2): 237-244.
[11] 范学军, 俞刚. 大庆RP-3航空煤油热物性分析[J]. 推进技术, 2006, 27(2): 187-192.(FAN Xue-jun, YU Gang.Analysis of Thermophysical Properties of Daqing RP-3 Aviation Kerosene[J].Journal of Propulsion Technology, 2006, 27(2): 187-192.)
[12] Lin K C, Kennedy P J, Jackson T A. Structures of Water Jets in a Mach 1.94 Supersonic Crossflow[R]. AIAA 2004-0971.
[13] 黄勇, 林宇震. 燃烧与燃烧室[M]. 北京: 北京航空航天大学出版社, 2008.
[14] Ely J F, Huber M L. NIST Standard Reference Database4-NIST Thermophysical Properties of Hydrocarbon Mixtures[M].Gaithersburg: National Inst.of standards,1990.
[15] Philippe Dagaut, Michel Cathonnet. The Ignition, Oxidation, and Combustion of Kerosene: a Review of Experimental and Kinetic Modeling[J]. Progress in Energy and Combustion Science, 2006, 32: 48-92.
[16] Horing D C, Davidson D F, Hanson R K. Study of the High-Temperature Autoignition of n-Alkane/O₂/Ar Mixture[J]. Journal of Propulsion and Power, 2002, 18(2): 363-371.
[17] Robert D Ingebo, Hampton H Foster. Drop-Size Distribution for Crosscurrent Breakup of Liquid Jets in Airstreams[M].USA: National Advisory Committee for Aeronautics, 1957. (编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2014-04-02；修订日期:2014-06-10。作者简介:吴显(1990—),男,硕士生,研究领域为超声速燃烧。E-mail:wuxian139@126.com