涡轮基组合循环发动机超级燃烧室燃烧性能试验

朱志新; 何小民; 薛冲; 洪亮; 秦伟林

doi:10.13224/j.cnki.jasp.2015.09.009

涡轮基组合循环发动机超级燃烧室燃烧性能试验

doi: 10.13224/j.cnki.jasp.2015.09.009

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 中国航天科工集团北京动力机械研究所高超声速冲压发动机技术重点实验室, 北京 100074

基金项目:

江苏省普通高校研究生科研创新计划(CXZZ13_0179)

详细信息

作者简介:
朱志新(1987-),男,江苏如皋人,博士生,主要从事航空发动机燃烧室和燃烧理论的研究.

中图分类号: V236
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出版历程
- 收稿日期: 2014-03-12
- 刊出日期: 2015-09-28

Experiment on performance of a hyper-combustor utilized in turbine based combined cycle engine

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Science and Technology on Scramjet Laboratory, Beijing Power Machinery Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China

摘要

摘要: 对涡轮基组合循环(turbine based combined cycle,TBCC)发动机超级燃烧室进行了试验研究.首先设计了超级燃烧室模型及相关的试验系统,并在此基础上开展了不同进口速度系数、温度和油气比下点火特性、贫油熄火特性和燃烧效率等燃烧室性能的试验研究.研究结果表明:随着内涵进口速度系数(0.10~0.25)的增加,点火当量比先减小后增加,熄火当量比逐渐增加,燃烧效率提高;随着内涵进口温度(573~873K)的增加,点火当量比和熄火当量比减小,燃烧效率提高;随外涵进口速度系数、温度的增加,燃烧效率提高.试验中获得最小点火当量比为0.984,最小熄火当量比为0.6.
- 涡轮基组合循环 /
- 超级燃烧室 /
- 火焰稳定器 /
- 燃烧试验 /
- 燃烧性能
Abstract: Experiments were conducted on a hyper-combustor of the turbine based combined cycle engine. First a model hyper-combustor rig and experimental system were designed, and then experiments were conducted to study the combustion performance including ignition characteristic, lean blowout characteristic and combustion efficiency under different inlet velocity coefficient, inlet temperature and fuel/air ratio(FAR). The test results show that the ignition equivalence ratio firstly decreases and then increases,lean blowout equivalence ratio and combustion efficiency increase with the turbo duct inlet velocity coefficient increasing from 0.10 to 0.25.The ignition and lean blowout equivalence ratio decrease and combustion dfficiency increases when the turbo duct inlet temperature increasing from 573K to 873K. Similarly the combustion efficiency increases when the bypass duct inlet velocity coefficient or temperature increases. The minimum ignition and lean blowout equivalence ratio obtained from the experiment is 0.984 and 0.6 respectively.
- turbine based combined cycle /
- hyper-combustor /
- flame holder /
- combustion experiment /
- combustion performance

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参考文献(18)

[1]	陈大光.高超声速飞行与TBCC方案简介[J].航空发动机,2006,32(3):10-13. CHEN Daguang.Brief introduction of hypersonic flight and TBCC concept[J].Aeroengine,2006,32(3):10-13.(in Chinese)
[2]	陈敏,唐海龙,朱大明,等.高超声速串联式组合动力装置方案[J].北京航空航天大学学报,2007,33(3):265-268. CHEN Min,TANG Hailong,ZHU Daming,et al.Hypersonic combined cycle engine concept with tandem layout[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(3):265-268.(in Chinese)
[3]	Ichimaru O,Ishizuka M,Murashima K.Overview of the Japanese national project for super/hypersonic transport propulsion system[R].ASME92-GT-252,1992.
[4]	Thomas S,Walker J F,Pittman J L.Overview of the turbine based combined cycle discipline[R].Atlanta,G A,U.S:NASA,2009 Annual Meeting,E-17625,2009.
[5]	岑可法,姚强,骆仲泱,等.高等燃烧学[M].杭州:浙江大学出版社,2000.
[6]	Miyagi H,Miyagawa H,Monji T,et al.Combine cycle engine research on Japanese HYPR project[R].AIAA 95-2751,1995.
[7]	Testsuji F,Kiyoshi I.HYPR90-T turbo engine research for HST combined cycle engine[R].SAE-951991,1995.
[8]	Miyagi H,Kimura H,Kishi K,et al.Combined cycle engine research in Japanese HYPR program[R].AIAA-98-3278,1998.
[9]	Bartolotta P A,Shafer D G.High speed turbines:development of a turbine accelerator(RTA) for space access[R].AIAA 2003-6943,2003.
[10]	Lee J H,Buehrle R.The GE-NASA RTA hyperburner design and development[R].NASA/TM-2005-213803,2005.
[11]	Davoudzadeh F,Buehrle R,Liu N S,et al.Numerical simulation of the RTA combustion rig[R].MASA/TM-2005-213899,2005.
[12]	McNelis N,Bartolotta P.Revolutionary turbine accelerator (RTA) demonstrator[R].AIAA 2005-3250,2005.
[13]	《航空发动机设计手册》总编委会.航空发动机设计手册:第11册加力燃烧室[M].北京:航空工业出版社,2000.
[14]	金莉,谭永华.火焰稳定器综述[J].火箭推进,2006,32(1):30-34. JIN Li,TAN Yonghua.Study on flameholders[J].Journal of Rocket Propulsion,2006,32(1):30-34.(in Chinese)
[15]	杜一庆.高温、低阻、高效加力燃烧室火焰稳定器机理研究[D].武汉:华中科技大学,2005. DU Yiqing.Mechanism investigation on aircraft afterburner flameholder of high efficiency,low drag and high temperature resistance[D].Wuhan:Huazhong University of Science and Technology,2005.(in Chinese)
[16]	许军民.冲压发动机燃烧室火焰稳定器试验研究和数值模拟[D].西安:西安电子科技大学,2007. XU Junmin.Experimental and numerical simulation of flameholders in a ramjet combustor[D].Xi'an:Xidian University,2007.(in Chinese)
[17]	张彭岗.典型稳定器和先进值班稳定器试验研究[D].南京:南京航空航天大学,2005. ZHANG Penggang.Experimental research on typical and advanced pilot flameholder in afterburner[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese)
[18]	叶超.冲压燃烧室关键部件方案设计与性能验证试验研究[D].南京:南京航空航天大学,2008. YE Chao.Design of key components and performance assessment test for ramjet combustor[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)