中心分级燃烧室预燃级燃烧性能实验

付镇柏; 林宇震; 张弛; 许全宏

doi:10.13224/j.cnki.jasp.2015.01.007

中心分级燃烧室预燃级燃烧性能实验

doi: 10.13224/j.cnki.jasp.2015.01.007

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实验室, 北京 100191

详细信息

作者简介:
付镇柏(1987-),男,山东济宁人,博士生,主要从事航空发动机燃烧方面研究.

中图分类号: V231.2
计量
- 文章访问数: 2332
- HTML浏览量: 6
- PDF量: 1158
- 被引次数: 0
出版历程
- 收稿日期: 2013-08-28
- 刊出日期: 2015-01-28

Experiment of combustion performance of internally-staged combustor pilot stage

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

摘要

摘要: 研究了一种中心分级燃烧室.在某大推力航空发动机慢车工况下,采用单头部矩形燃烧室,进行了燃烧性能实验,考察了预燃级旋流杯套筒扩张角、台阶高度、预燃级气量分配对污染排放、燃烧效率和贫油熄火油气比的影响作用.实验结果表明:慢车工况下,预燃级旋流杯套筒扩张角从60°增大到100°后,NOx排放降低42%,CO和未燃碳氢燃料(UHC)排放均增加2.5倍左右,燃烧效率降低1.75%,贫油熄火油气比从0.0038增大到0.0067;台阶高度减小24%后,NOx排放降低37%,CO和UHC排放分别增加1.5倍和1.2倍,燃烧效率降低1.32%,贫油熄火油气比从0.0042增大到0.0061;预燃级气量分配减小20%后,NOx排放增加13.5%,CO和UHC排放分别降低55.6%和38.9%,燃烧效率增大1.46%,贫油熄火油气比从0.0061减小到0.0051.
- 航空发动机 /
- 中心分级燃烧室 /
- 预燃级 /
- 旋流杯 /
- 台阶高度 /
- 燃烧性能
Abstract: A internally-staged combustor was studied. The combustion performance experiments using a single module rectangular combustor were performed under the idle condition of a large thrust aero-engine. The effects of flare angles of pilot swirl cup, step heights and pilot airflow rates on pollution emissions, combustion efficiency and lean blowout fuel/air ratio (LBO FAR) were investigated experimentally. The experimental results indicate that under the idle condition, NOx emission can decrease by 42% with CO, unborn hydrocarbon (UHC) emissions increasing by 2.5 times, combustion efficiency decreasing by 1.75% and LBO FAR increasing from 0.0038 to 0.0067 when the flare angle of pilot swirl cup increases from 60 degree to 100 degree; NOx emission can decrease by 37% with CO, UHC emissions increasing by 1.5 and 1.2 times, respectively, combustion efficiency decreasing by 1.32% and LBO FAR increasing from 0.0042 to 0.0061 when the step height decreases by 24%; NOx emission can increase by 13.5% with CO, UHC emissions decreasing by 55.6% and 38.9%, respectively, combustion efficiency increasing by 1.46% and LBO FAR decreasing from 0.0061 to 0.0051 when the pilot airflow rate decreases by 20%.
- aero-engine /
- internally-staged combustor /
- pilot stage /
- swirl cup /
- step height /
- combustion performance

HTML

参考文献(25)

[1]	Birch N T.2020 vision:the prospects for large civil aircraft propulsion[R].International Council of Aeronautical Sciences,ICAS 2000-1.1.1,2000.
[2]	彭云晖,许全宏,张弛,等.我国大飞机发动机低污染燃烧室发展考虑[R].北京:中国航空学会2007年学术年会,2007.
[3]	International Civil Aviation Organization.International standards and recommended practices environmental protection annex 16 to the convention on international civil aviation:Volume Ⅱ aviation engine emissions[R].Convention on International Civil Aviation-Doc7300,1993.
[4]	林宇震,许全宏,刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社,2008.
[5]	Committee on Aviation Environmental Protection.Report of the independent experts to CAEP8 on the second NOx review & long term technology goals[R].ICAO Working Paper CAEP/8-WP/10,2010.
[6]	Foust M J,Thomsen D.Development of the GE aviation low emission TAPS combustor for next generation aircraft engines[R].AIAA-2012-0936,2012.
[7]	Lazik W,Doerr T,Bake B.Low NOx combustor development for the engine 3E core engine demonstrator[R].International Society for Air Breathing Engines,ISABE2007-1190,2007.
[8]	Yamamoto T,Shimodaira K,Krosawa Y,et al.Research and development of staging fuel nozzle for aero-engine[R].ASME Paper 2009-GT-59852,2009.
[9]	Mongia H C.TAPS:a 4th generation propulsion combustor technology for low emissions[R].AIAA-2003-2657,2003.
[10]	Dhanuka S K,Driscoll J F,Mongia H C.Instantaneous flow structures in a reacting gas turbine combustor[R].AIAA-2008-4683,2008.
[11]	Dhanuka S K,Temme J E,Driscoll J F,et al.Unsteady aspects of lean premixed-prevaporized (LPP) gas turbine combustor:flame-flame interactions[R].AIAA-2010-1148,2010.
[12]	Dhanuka S K,Temme J E,Driscoll J F,et al.Vortex-shedding and mixing layer effects on periodic flashback in a lean premixed prevaporized gas turbine combustor[J].Proceedings of the Combustion Institute,2009,32(2):2901-2908.
[13]	Lazik W,Doerr T,Bake S,et al.Development of lean-burn low-NOx combustion technology at Rolls-Royce Deutschland[R].ASME Paper 2008-GT-51115,2008.
[14]	Yamamoto T,Shimodaira K,Krosawa Y,et al.Investigations of a staged fuel nozzle for aero-engines by multi-sector combustor test[R].ASME Paper 2010-GT-23206,2010.
[15]	Matsuyama R,Kobayashi M,Ogata H,et al.Development of a lean staged combustor for small aero-engines[R].ASME Paper 2012-GT-68272,2012.
[16]	Fujiwara H,Shimodaira K,Hayashi S,et al.Suppression of NOx emission of a lean staged combustor for an aircraft engine[R].ASME Paper 2011-GT-46256,2011.
[17]	Kobayashi M,Ogata H,Oda T,et al.Improvement on ignition performance for a lean staged low NOx combustor[R].ASME Paper 2011-GT-46187,2011.
[18]	颜应文,李红红,赵坚行,等.双环预混旋流低污染燃烧室数值模拟[J].航空动力学报,2009,24(9):1923-1929. YAN Yingwen,LI Honghong,ZHAO Jianxing,et al.Numerical study of low emissions for twin annular premixing swirler combustor[J].Journal of Aerospace Power,2009,24(9):1923-1929.(in Chinese)
[19]	刘富强,杨金虎,刘存喜,等.燃油分级多点喷射低污染燃烧室的化学反应网络模型分析[J].工程热物理学报,2012,33(3):537-541. LIU Fuqiang,YANG Jinhu,LIU Cunxi,et al.Analysis of chemical reactor network for a low emission combustor with fuel staged multi-point injection[J].Journal of Engineering Thermophysics,2012,33(3):537-541.(in Chinese)
[20]	颜应文,徐榕,邓远灏,等.贫油预混预蒸发燃烧室头部流场研究[J].航空学报,2012,33(6):965-976. YAN Yingwen,XU Rong,DENG Yuanhao,et al.Flow field study for head of lean premixed prevaporized low-emission combustor[J].Acta Aeronautica et Astronautica Sinica,2012,33(6):965-976.(in Chinese)
[21]	徐榕,赵坚行,刘勇,等.TAPS/MLDI低污染燃烧室油雾特性[J].航空动力学报,2012,27(11):2421-2428. XU Rong,ZHAO Jianxing,LIU Yong,et al.Fuel spray characteristic of TAPS/MLDI low emission combustion[J].Journal of Aerospace Power,2012,27(11):2421-2428.(in Chinese)
[22]	FU Zhenbo,LI Jibao,LIN Yuzhen.Experimental investigation on ignition performance of LESS combustor[R].ASME Paper 2011-GT-45786,2011.
[23]	付镇柏,林宇震,张弛,等.中心分级燃烧室进场工况燃油分级方式试验研究[J].推进技术,2014,35(1):77-86. FU Zhenbo,LIN Yuzhen,ZHANG Chi,et al.Experimental investigation on fuel-staging mode of the internally-staged combustor under the approach condition[J].Journal of Propulsion Technology,2014,35(1):77-86.(in Chinese)
[24]	《航空发动机设计手册》总编委会.航空发动机设计手册:第9分册[M].北京:航空工业出版社,2000.
[25]	航空航天工业部.高效节能发动机文集:第4分册[M].北京:航空工业出版社,1991.