中心分级燃烧室耦合回流区贫油熄火机理

邹博文; 许全宏; 曹文宇; 张弛; 林宇震

中心分级燃烧室耦合回流区贫油熄火机理

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

计量
- 文章访问数: 1721
- HTML浏览量: 18
- PDF量: 1349
- 被引次数: 0
出版历程
- 收稿日期: 2012-07-20
- 刊出日期: 2013-08-28

Lean blowout mechanism of coupled recirculation zone in concentric 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: 针对中心分级模型燃烧室开展了常压贫油熄火试验和慢车状态贫油熄火试验,并结合贫油熄火时的主/预燃级耦合回流区流场数值模拟分析了该燃烧室的贫油熄火机理.结果表明:与常规燃烧室的贫油熄火机理不同,中心分级燃烧室的贫油熄火油气比是由预燃级和主燃级共同形成的耦合回流区所决定的.耦合回流区的回流量主要由主燃级回流主导,在该研究的中心分级燃烧室结构下,回流区从主燃级卷吸的气量是预燃级本身气量的4.3倍,导致按预燃级气量计算的熄火当量比达到2~2.5,远高于常规燃烧室头部的熄火当量比0.4~0.5.
- 航空发动机 /
- 燃烧室 /
- 中心分级 /
- 贫油熄火 /
- 回流区
Abstract: Experiments under atmosphere and idle states were carried out to analyze the mechanism of lean blowout by numerical simulation of coupled recirculation zone formed in main stage and pilot stage.The results show that unlike conventional combustor,the lean blowout fuel-air ratio of concentric staged combustor is determined by coupled recirculation zone formed by pilot and main swirlers.The recirculating flow in the coupled zone is dominated by the main stage in this concentric staged combustor,and air entrainment from the main stage is 4.3 times of that from the pilot stage itself,leading to the lean blowout equivalence ratio of pilot stage up to 2 to 2.5,far higher than that of 0.4 to 0.5 of conventional combustor dome.
- aircraft engine /
- combustor /
- concentric staged /
- lean blowout /
- recirculation zone

HTML

参考文献(15)

[1]	Bahr D W.Technology for design of high temperature rise combustors[J].Journal of Propulsion and Power,1987,3(2):179-186.
[2]	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.
[3]	林宇震,林阳,张弛.先进燃烧室分级燃烧空气流量分配的探讨[J].航空动力学报,2010,25(9):1923-1930. LIN Yuzhen,LIN Yang,ZHANG Chi.Discussion on combustion airflow distribution of advanced staged combustor[J].Journal of Aerospace Power,2010,25(9):1923-1930.(in Chinese)
[4]	Mongia H C.Engineering aspects of complex gas turbine combustion mixers:Part Ⅰ high ΔT [R].AIAA 2011-107,2011.
[5]	Mongia H C.TAPS:a 4th generation propulsion combustor technology for low emissions [R].AIAA 2003-2657,2003.
[6]	Mongia H C.Perspective of combustion modeling for gas turbine combustors [R].AIAA 2004-156,2004.
[7]	Sulabh K D,Jacob E T,Driscoll J F,et al.Unsteady aspects of lean premixed-prevaporized (LPP) gas turbine combustors:flame-flame interactions [R].AIAA 2010-1148,2010.
[8]	Sulabh K D,James F D.Instantaneous flow structures in a reacting gas turbine combustor [R].AIAA 2008-4683,2008.
[9]	Mohammad B S,Jeng S M.Gas turbine combustor sector flow structure[J].Journal of Propulsion and Power,2011,27(3):710-717.
[10]	Lefebvre A H.Gas turbine combustion[M].2nd ed.Philadelphia:Talor & Francis Press,1999.
[11]	Meller A M.Design of modern turbine combustor[M].London:Academic Press,1990.
[12]	Mongia H C,Vermeersch M L,Held T J.Data reduction and analysis (DRA) for emissions and lean blowout [R].AIAA 2003-0823,2003.
[13]	徐华胜,黄义勇,王秀兰.喷嘴供油特性对双涡流器头部气动雾化效果的影响研究[J].燃气涡轮试验与研究,2004,17(2):14-18. XU Huasheng,HUANG Yiyong,WANG Xiulan.Study on the effect of fuel jet characteristics on airblast atomization performance for device with two-stage swirler[J].Gas Turbine Experiment and Research,2004,17(2):14-18.(in Chinese)
[14]	黄勇,郭志辉.某燃烧室头部旋流油雾场特性的实验研究[C]//中国航空学会第五届动力年会论文集.北京:中国航空学会动力专业分会,2003:103-110.
[15]	彭云晖,林宇震,许全宏,等.双旋流空气雾化喷嘴喷雾、流动和燃烧性能[J].航空学报,2008,29(1):1-13. PEN Yunhui,LIN Yuzhen,XU Quanhong,et al.Atomization,aerodynamics and combustion performance of swirl cup[J].Acta Aeronautica et Astronautica Sinica,2008,29(1):1-13.(in Chinese)