超燃发动机混合效率评估方法探讨

张弯洲; 乐嘉陵; 田野; 杨顺华; 邓维鑫; 程文明

超燃发动机混合效率评估方法探讨

1.
西南交通大学机械工程学院, 成都 610031
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

基金项目: 自然科学青年科学基金(10902109)

计量
- 文章访问数: 1909
- HTML浏览量: 166
- PDF量: 663
- 被引次数: 0
出版历程
- 收稿日期: 2012-03-20
- 刊出日期: 2012-09-28

Evaluation methods of the fuel mixing efficiency for Scramjet

1.
School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610031, China
2.
Airbreathing Hypersonics Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 总结和分析了3种常用的典型混合效率评估方法,为了提高对混合程度的评估精度和客观性,提出了3种新的混合程度评估方法和指标:流场混合效率,可燃混合效率和适燃区域比例.流场混合效率能够客观评估流场结构的混合性能和增混措施的效果;可燃混合效率和适燃区域比例,结合了流场中的熄火边界参数,能够将燃料的分布及混合程度直接与点火燃烧联系,能够客观评估不同程度的贫油和富油流场的混合程度,能够合理地预测燃烧可能发生的区域.最后通过二维算例比较了新旧方法的评估结果,验证了新评估方法的合理性.
- 燃料混合 /
- 超燃发动机 /
- 点火燃烧 /
- 混合效率 /
- 超燃发动机设计
Abstract: Three commonly-used evaluation methods for scramjet were summarized and analyzed,to improve the precision and objectivity for mixing evaluation,three new methods were imposed:the flow-field mixing efficiency,the flammable mixing efficiency and the flammable region percentage.The flow-field mixing efficiency can estimate the mixing performance of the flow structure and the effect of the mixing enhancement measurements.The flammable mixing efficiency and the flammable region percentage that took the flow-field blowout limits into consideration can connect with the ignition and combustion directly,objectively estimate the mixing efficiency for different lean and rich regions,and predict the region that combustion may occur.Then the three methods are verified and compared with the existed methods by two-dimension computational cases.
- fuel mixing /
- scramjet /
- ignition and combustion /
- mixing efficiency /
- design of scramjet

HTML

参考文献(18)

[1]	Heiser W H,Prattt D T.Hypersonic airbreathing propulsion[M].Washington,DC:American Institute of Aeronautics and Astronautics Inc.,1994.
[2]	SegalC.The scramjet engine:processes and characteristics[M].New York:Cambridge University Press,2009.
[3]	刘世杰,潘余,刘卫东.超燃冲压发动机支板喷射燃料的燃烧过程试验[J].航空动力学报,2009,24(1):55-59. LIU Shijie,PAN Yu,LIU Weidong.Experimental study on the combustion and flow process in a scramjet with strut injector[J].Journal of Aerospace Power,2009,24(1):555-559.(in Chinese)
[4]	Lin K C,Kendedy P J,Jackson T A.Structures of aerated-liquid jets in high-speed crossflows. AIAA 2002-3178,2002.
[5]	Hirano K,Matsuo A,Kouchi T,et al.New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. AIAA 2007-5028,2007.
[6]	WANG Dian,SONG Wenyan,LI Jianping,et al.Investigation of hydrocarbon-fuel ignition and combustion in scramjet combustor[J].Journal of Solid Rocket Technology,2008,31(5):449-452.
[7]	Liscinsky D S,True B,Holdeman M A.Crossflow mixing of noncircal jets. AIAA-95-0732,1995.
[8]	Fuller R P,Wu P K,Nejad A S,et al.Comparison of physical and aerodynamic ramps as fuel injectors in supersonic flow[J].Journal of Propulsion and Power,1998,14(2):135-145.
[9]	Kopchenov V I,Lomkov K E.The enhancement of the mixing and combustion processes applied to scramjet engines. AIAA-92-3428,1992.
[10]	Rogers R C.Mixing of hydrogen injected from multiple injectors normal to a supersonic airstream. NASA TN D-6476,1971.
[11]	Ringins D W,McClinton R C.A computational investigation of mixing and reaction flows in supersonic combustors. AIAA-92-0626,1992.
[12]	Parent B,Sislian J P.Turbulent hypervelocity fuel/air mixing by cantilevered ramp injectors. AIAA-2001-1888,2001.
[13]	Yang V,Li J,Yeol J,et al.Ignition transient in an ethylene fueled scramjet engine with air throttling Part Ⅰ:non-reacting flow development and mixing. AIAA 2010-409,2001.
[14]	Rasmussen C C,Driscoll J F,Hsu K Y,et al.Stability limits of cavity-stabilized flames in supersonic flow[J].Proceedings of the Combustion Institute,2005,30(2):2825-2833.
[15]	陈立红,顾洪斌,张新宇.支板凹腔一体化超燃冲压发动机实验研究[J].工程热物理学报,2007,28(4):717-719. CHEN Lihong,GU Hongbin,ZHANG Xinyu.Experimental study on scramjet with cavity/strut configuration[J].Journal of Engineering Thermophysics,2007,28(4).
[16]	Doster J C,King P I,Gruber M R,et al.Pylon fuel injector design for a scramjet combustor. AIAA 2007-5404,2007.
[17]	Ben-Yakar A,Hanson R K.Cavity flame-holder for ignition and flame stabilization in scramjet:an overview[J].Journal of Propulsion and Power,2001,17(4):869-877.
[18]	Aso S,Yamane Y,Umii K,et al.A study on supersonic mixing flow-field with swept ramp injectors. AIAA 97-0397,1997.