不同台阶高度对中心分级燃烧室点火熄火性能的影响

付镇柏; 林宇震; 傅奇慧; 张弛

不同台阶高度对中心分级燃烧室点火熄火性能的影响

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: 1258
- HTML浏览量: 0
- PDF量: 1035
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-05
- 刊出日期: 2014-05-28

Effect of different step heights on ignition and blowout performance of internally-staged combustor

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: 设计了一种贫油燃烧中心分级燃烧室，采用单头部矩形试验件，试验研究了3种不同台阶高度对点火熄火性能的影响.试验中只有预燃级喷嘴供油工作，在常温常压、常温低压条件下进行了贫油点火试验，在常温常压、加温常压下进行了贫油熄火试验.结果表明：台阶高度越大，贫油点火边界越宽，同时贫油熄火边界越宽；进口温度的升高有助于改善贫油熄火性能，并缩小3种方案贫油熄火油气比的差距，在320~570K的进口温度范围内，贫油熄火油气比的最大差距由40%减小到13%；3种方案都具有较好的常温负压点火性能，且在0.5%~1.5%的火焰筒进出口总压降下，贫油点火油气比差异不大，最大相差不超过10%.
- 低污染 /
- 中心分级燃烧室 /
- 点火 /
- 熄火 /
- 台阶高度
Abstract: A lean-burn internally-staged combustor was designed.Using a single module rectangular test article,the effects of three different step heights on ignition and blowout performance were studied herein.Only the pilot stage nozzle was fueled in the tests.The lean ignition test was operated with normal and negative inlet pressures under normal inlet temperatures condition,and the lean blowout test was operated with the normal and raised inlet temperature under the normal inlet pressure condition.The experimental results indicate that the lean ignition and blowout boundaries are simultaneously widened with the increasing the step height;the inlet temperature rise is good for lean blowout performance with narrowing the lean blowout fuel air ratio differences in these three cases,and the maximum differences decrease from 40% to 13% under the test condition of the inlet temperature of 320-570K;the ignition performance under the negative inlet pressure and normal inlet temperature condition is rather good for all three cases with little difference of the lean ignition fuel air ratio,and the maximum differences don't exceed 10% under the test condition of the liner total pressure drop of 0.5%-1.5%.
- low pollution /
- internally-staged combustor /
- ignition /
- blowout /
- step height

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:大型飞机关键技术高层论坛暨中国航空学会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 Ⅱaviation engine emissions[R].Convention on International Civil Aviation-Doc7300, 1993.
[4]	Lefebvre A H.Gas turbine combustion[M].2nd ed.Philadelphia:Taylor and Francis, 1999.
[5]	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.
[6]	Mongia H C, Dodds W.Low emissions propulsion engine combustor technology evolution:past, present and future[R].International Council of Aeronautical Sciences, ICAS2004-6.9.2, 2004.
[7]	Committee on Aviation Environmental Protection.Report of the independent experts to CAEP/8 on the second NOx review and the establishment of medium and long term technology goals for NOx[R].International Civil Aviation Organization, ICAO 9953, 2010.
[8]	Foust M J, Thomsen D.Development of the GE aviation low emission TAPS combustor for next generation aircraft engines[R].AIAA-2012-0936, 2012.
[9]	Lazik W, Doerr T, Bake B.Low NOx combustor development for the engine 3E core engine demonstrator[R]. International Society for Air Breathing Engines, ISABE 2007-1190, 2007.
[10]	Mongia H C.TAPS:a 4th generation propulsion combustor technology for low emissions[R].AIAA-2003-2657, 2003.
[11]	Dhanuka S K, Driscoll J F, Mongia H C.Instantaneous flow structures in a reacting gas turbine combustor[R].AIAA-2008-4683, 2008.
[12]	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.
[13]	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.
[14]	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.
[15]	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.
[16]	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.
[17]	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.
[18]	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.
[19]	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.
[20]	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)
[21]	刘殿春, 董玉玺, 尚守堂, 等.单环腔中心分级燃烧室流场数值模拟[J].航空动力学报, 2010, 25(6):1251-1257. LIU Dianchun, DONG Yuxi, SHANG Shoutang, et al.Numerical simulation of the flow field in a single annular concentric staged combustor[J].Journal of Aerospace Power, 2010, 25(6):1251-1257.(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]	林宇震, 林培华, 许全宏, 等.复合式收扩套筒空气雾化喷嘴燃烧室点火研究[J].航空动力学报, 2007, 22(3):342-346. LIN Yuzhen, LIN Peihua, XU Quanhong, et al.Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve[J].Journal of Aerospace Power, 2007, 22(3):342-346.(in Chinese)
[24]	Mellor A M.Design of modern turbine combustors[M].London:Academic Press, 1990.
[25]	Law C K.Combustion physics[M].New York:Cambridge University Press, 2006.