直混燃烧与LPP组合燃烧室数值研究

刘强; 索建秦; 梁红侠; 黎明; 李瀚

直混燃烧与LPP组合燃烧室数值研究

西北工业大学动力与能源学院, 西安 710072

计量
- 文章访问数: 1670
- HTML浏览量: 139
- PDF量: 680
- 被引次数: 0
出版历程
- 收稿日期: 2011-10-26
- 刊出日期: 2012-11-28

Numerical investigation of combination of direct mixing combustion and LPP combustor

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 设计了直混燃烧与贫油预混预蒸发(LPP)组合的单管燃烧室.燃烧室头部采用同轴同旋向主模旋流器和副模旋流器结构,主、副油路分别采用直射式喷嘴和压力雾化喷嘴,可以在单管燃烧室上掌握和实现低污染燃烧排放控制技术,并采用Fluent软件对设计的单管燃烧室模型进行数值模拟.计算结果表明:主副模燃烧区相互独立;副模是直混燃烧,主要作用稳定火焰.主模是预混燃烧,燃烧区温度分布均匀,从而实现低NO_x排放.解决了大工况下低NO_x排放与慢车贫油熄火之间的矛盾.
- 燃烧室 /
- 低污染 /
- 数值模拟 /
- 贫油预混预蒸发 /
- 火焰稳定
Abstract: A combination of direct mixing combustion and lean premixed prevaporized(LPP) single-module tubular combustor was designed.Numerical investigation of the combustor was conducted with software fluent.The results show that main flame zone is independent from pilot flame zone;pilot module operates as a direct mixing flame for anchoring main flame.Main module operates as a premixed flame,providing a uniform temperature distribution in combustion zone,which reduces NO_x emissions.The contradiction was solved between the low NO_x emissions at high power conditions and flame stabilization at low power conditions.
- combustor /
- low emission /
- numerical simulation /
- lean premixed prevaporized /
- flame stabilization

HTML

参考文献(15)

[1]	Bulzan D,Lee C M.NASA propulsion system emissions reduction research [R].AIAA-2011-3529,2011.
[2]	Mongia H C.TAPS-A 4th generation propulsion combustor technology for low emissions [R].AIAA-2003-2657,2003.
[3]	Mckinney R G,Sepulveda D,Sowa W,et al.The pratt & whitney TALON X low emissions combustor:revolutionary results with evolutionart technology [R].AIAA-2007-386,2007.
[4]	金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1988.
[5]	严传俊,范玮.燃烧学[M].西安:西北工业大学出版社,2008.
[6]	张川,索建秦,金如山.民用飞机低污染燃烧室的技术成熟度划分[J].航空工程进展,2010,1(1): 85-89. ZHANG Chuan,SUO Jianqin,JIN Runshan.Technology readiness level scale for low emission combustor of civil aircraft[J].Advances in Aeronautical Science and Engineering,2010,1(1):85-89.(in Chinese)
[7]	Becker J,Hassa C.Liquid fuel placement and mixing of generic aero enging premix module at different operating conditions[J].Journal of Engineering for Gas Turbine and Power,2003,125(10):901-908.
[8]	汪涛,索建秦,梁红侠,等.火焰筒切向进气发散小孔冷却数值模拟[J].航空动力学报,2011,26(5):1052-1058. WANG Tao,SUO Jianqin,LIANG Hongxia,et al.Numerical study of tangential effusion cooling for combustor liner[J].Journal of Aerospace Power,2011,26(5):1052-1058.(in Chinese)
[9]	Lyons V J.Fuel/air nonuniformity:effect on oxide emissions [R].AIAA-81-0327R,1981.
[10]	颜应文,宋双文,胡好生,等.折流燃烧室两相喷雾燃烧流场数值模拟[J].航空动力学报,2011,26(5):1003-1010. YAN Yingwen,SONG Shuangwen,HU Haosheng,et al.Numerical investigations of two-phase spray combustion flow fields in slinger annular combustor[J].Journal of Aerospace Power,2011,26(5):1003-1010.(in Chinese)
[11]	颜应文,李红红,赵坚行,等.双环预混旋流低污染燃烧室数值研究[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)
[12]	Nicol D G,Steele R C,Marinov N M,et al.The importance at the Nitrous Oxide pathway to NO_x in lean-premixed combustion[J].Journal of Engineering for Gas Turbine and Power,1995,117(1):100-111.
[13]	岑可法,姚强.高等燃烧学[M].杭州:浙江大学出版社,2000.
[14]	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.
[15]	Chigier N A,Chervinsky A.Aerodynamic study of turbulent burning free jets with swirl[J].Symposium (International)on Combustion,1967,11(1):489-499.