冲压发动机驻涡燃烧室燃烧性能试验

何小民; 秦伟林; 朱志新; 牛志刚; 费立群; 彭力; 杨承宇

doi:10.13224/j.cnki.jasp.2015.01.003

冲压发动机驻涡燃烧室燃烧性能试验

doi: 10.13224/j.cnki.jasp.2015.01.003

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. 中国航天科工集团公司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:

高超声速冲压发动机技术重点实验室开放基金

南京航空航天大学博士学位论文创新与创优基金(BCXJ14-01)

详细信息

作者简介:
何小民(1971-),男,浙江义乌人,教授,博士,主要从事航空航天动力燃烧理论和燃烧技术的研究.

中图分类号: V235.21
计量
- 文章访问数: 2487
- HTML浏览量: 2
- PDF量: 1123
- 被引次数: 0
出版历程
- 收稿日期: 2013-09-09
- 刊出日期: 2015-01-28

Experiment on combustion performance of ramjet engine withtrapped-vortex combustor

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 Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China

摘要

摘要: 针对某冲压发动机驻涡燃烧室模型,进行了不同进口温度、进口速度系数和余气系数下燃烧室燃烧性能的试验研究,研究结果证明:随着进口速度系数的增加(0.20~0.35),点火总油气比和贫油熄火油气比增加,燃烧效率变化不明显;随着进口温度的增加(573~773K),点火总油气比和贫油熄火油气比下降,燃烧效率提高;随着余气系数的增加(1.1~2.1),燃烧效率提高.试验中获得最小点火总油气比为0.0035,最小贫油熄火油气比为0.0028,最高燃烧效率93%.研究证明了驻涡应用于冲压发动机燃烧室的可行性.
- 冲压发动机 /
- 驻涡 /
- 燃烧室 /
- 燃烧性能 /
- 进口气动参数
Abstract: Experiments were conducted to study the combustion performance of ramjet engine model with trapped-vortex combustor under different inlet temperatures and velocity coefficients. The results show: with the increase of inlet velocity coefficient increases (0.20-0.35), the ignition and lean blowout fuel air ratios rise, and the combustion efficiency changes little. As the inlet temperature increases(573-773K), the ignition fuel air ratio and lean blowout fuel air ratio decreases, and the combustion efficiency increases varying with increase of the excess air coefficient(1.1-2.1). The minimum ignition fuel air ratio and the lean blowout fuel air ratio is 0.0035 and 0.0028 respectively, the maximum combustion efficiency obtained from experiment is 93%.The results prove the feasibility of applying the cavity to the ramjet combustor.
- ramjet engine /
- trapped-vortex /
- combustor /
- combustion performance /
- inlet aerodynamic parameter

HTML

参考文献(17)

[1]	李庆,潘余,李清廉,等.基于凹腔火焰稳定器的亚燃冲压发动机燃烧室点火过程研究[J].宇航学报,2009,30(4):1600-1605. LI Qing,PAN Yu,LI Qinglian,et al.Ignition characterristics of ramjet with cavity-based flameholder[J].Journal of Astronautics,2009,30(4):1600-1605.(in Chinese)
[2]	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)
[3]	韩启祥,王家骅.沙丘驻涡蒸发式稳定器低压性能的试验研究[J].推进技术,2001,22(1):40-42. HAN Qixiang,WANG Jiahua.Experimental investingation on performance of vapor barchane dune vortex flame-holder at low pressure[J].Journal of Proplusion Technology,2001,22(1):40-42.(in Chinese)
[4]	杨茂林,全中,白兴艳,等.尾缘吹气式火焰稳定器试验研究[J].航空动力学报,1998,13(2):185-188. YANG Maolin,QUAN Zhong,BAI Xingyan,et al.Experimental investigation on EBMC flameholder[J].Journal of Aerospace Power,1998,13(2):185-188.(in Chinese)
[5]	Kim S D,Jeung I.Numerical simulation on a reacting flows of coaxial ramjet dump combustor with liquid fuel injection[R].AIAA-2006-4749,2006.
[6]	刘巍,杨涛.固体燃烧冲压发动机旋流冷态流场数值模拟研究[J].航空动力学报,2009,24(3):711-716. LIU Wei,YANG Tao.Numerical simulation of cold swirl flow field for solid fuel ramjet[J].Journal of Aerospace Power,2009,24(3):711-716.(in Chinese)
[7]	丁猛,王振国.凹腔火焰稳定器阻力特性的实验研究[J].航空学报,2006,27(4):556-560. DING Meng,WANG Zhenguo.Experimental investigation on the drag of cavity flame holder[J].Acta Aeronautica et Astronautica Sinica,2006,27(4):556-560.(in Chinese)
[8]	Roquemore W M,Shouse D,Burrus D,et al.Trapped vortex combustor concept for gas turbines[R].AIAA-2001-0483,2001.
[9]	Lee J,Winslow R,Buehrle R J.The GE-NASA RTA hyperburner design and development[R].NASA/TM-2005-213803,2005.
[10]	席文雄.亚燃冲压发动机燃烧室数值仿真与试验研究[D].长沙:国防科学技术大学,2008. XI Wenxiong.Numerical and experimental research on the ramjet combustor based on cavity[D].Changsha:National University of Defense Technology,2008.(in Chinese)
[11]	费立群,张炎,牛志刚,等.冲压发动机驻涡燃烧室模型方案数值模拟研究[J].推进技术,2011,32(5):676-679. FEI Liqun,ZHANG Yan,NIU Zhigang,et al.Numerical simulation on trapped-vortex combustor model for ramjet engine[J].Journal of PropulsionTechnology,2011,32(5):676-679.(in Chinese)
[12]	吴迪,金捷,季鹤鸣.一种加力燃烧室凹腔支板火焰稳定方案研究[C]//中国航空学会第七届动力年会论文集.贵州:中国航空学会,2010:657-660.
[13]	金义,何小民,蒋波.富油燃烧/快速淬熄/贫油燃烧(RQL)工作模式下驻涡燃烧室排放性能试验[J].航空动力学报,2011,26(5):1031-1036. JIN Yi,HE Xiaomin,JIANG Bo.Experimental study on emission performance of rich-burn quick-quench lean-burn (RQL) trapped-vortex combustor[J].Journal of Aerospace Power,2011,26(5):1031-1036.(in Chinese)
[14]	JIN Yi,HE Xiaomin,ZHANG Jinyu,et al.Experimental study on emission performance of an LPP/TVC[J].Chinese Journal of Aeronautics,2012,25(3):335-341.
[15]	秦伟林,何小民,金义,等.凹腔驻涡与支板稳焰组合加力燃烧室模型冷态流场试验[J].航空动力学报,2012,27(6):1347-1354. QIN Weilin,HE Xiaomin,JIN Yi,et al.Experimental investigation on cold flow characteristics of afterburner with cavity/strut hybrid flameholders[J].Journal of Aerospace Power,2012,27(6):1347-1354.(in Chinese)
[16]	《航空发动机设计手册》总编委会.航空发动机设计手册:第11分册加力燃烧室[M] 北京:航空工业出版社,2001.
[17]	沈维道,童钧耕.工程热力学[M].北京:高等教育出版社,2000.