头部及掺混孔对三级旋流器燃烧室出口温度分布影响的试验

丁国玉; 何小民; 薛冲; 洪亮

doi:10.13224/j.cnki.jasp.2015.04.006

头部及掺混孔对三级旋流器燃烧室出口温度分布影响的试验

doi: 10.13224/j.cnki.jasp.2015.04.006

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

基金项目:

江苏省普通高校研究生科研创新计划(CXLX12_0169)

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:
丁国玉(1985-),男,山东潍坊人,博士生,主要从事航空发动机燃烧室和燃烧理论的研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2013-11-11
- 刊出日期: 2015-04-28

Experiment on effect of dome and dilution holes on outlet temperature distribution for triple swirler combustor

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 对4种不同三级旋流器方案和两种不同掺混孔排布方案的燃烧室在不同进口速度、油气比参数下的出口温度分布进行了常压试验研究,研究结果表明:各方案的出口温度分布系数随进口速度和油气比有所变化,但变化范围不大;中间旋流器与外旋流器旋向相反时,出口温度分布更为均匀;对于两种不同的旋流数组合0.7-1-1.5和1.5-1-0.8,前者出口温度分布系数对外旋流器旋向的改变更为敏感;与方案B相比,方案A的掺混孔排布更加适合该三级旋流器燃烧室;掺混孔排布要与头部结构相匹配,这样才能优化出口温度分布.
- 头部 /
- 掺混孔 /
- 三级旋流器 /
- 燃烧室 /
- 出口温度分布
Abstract: Experiments were conducted to study the outlet temperature distribution of combustor for four different triple swirler schemes and two different dilution holes arrangement schemes with different inlet velocities and fuel-air ratios at fixed atmospheric pressure. The results show that: the outlet temperature distribution factors of different schemes change little with the inlet velocity and fule-ratio ratio; when intermediate swirler and outer swirler are counter-rotating, the outlet temperature distribution becomes more uniform; for two kinds of swirl number combination of 0.7-1-1.5 and 1.5-1-0.8, the outlet temperature distribution factor of the former is more sensitive to the change of outer swirler direction than that of the latter; compared with scheme B, the dilution holes arrangement of scheme A is more suitable for the triple swirler combustor; the dome and dilution holes arrangement should be matched properly in order to optimize the outlet temperature distribution.
- dome /
- dilution holes /
- triple swirler /
- combustor /
- outlet temperature distribution

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参考文献(19)

[1]	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.
[2]	Cox G B.An analytical model for predicting exit temperature profile from gas turbine engine annular combustors[R].AIAA 75-1307, 1975.
[3]	金如山.航空燃气轮机燃烧室[M].北京:宇航出版社, 1988.
[4]	丁国玉, 何小民, 金义, 等.主燃区出口特征影响出口温度场性能的数值研究[J].航空发动机, 2012, 38(4):17-21. DING Guoyu, HE Xiaomin, JIN Yi, et al.Influence of primary zone outlet feature on combustor outlet temperature field[J].Aeroengine, 2012, 38(4):17-21.(in Chinese)
[5]	McManus K, Edmond L.Adaptive closed-loop system for control of combustor pattern factor[R].AIAA 96-0843, 1996.
[6]	Miller M F, McManus K R, Allen M G, et al.An aerodynamic control system for modifying fuel spray distributions[R].AIAA-2000-0192, 2000.
[7]	Ziraksaz Mohammad H.Approaching the prototype can-combustors by combustion test[R].AIAA-2002-3869, 2002.
[8]	Chen Y, Scarborough D, Liang S, et al.Manipulating pattern factor using synthetic jet actuators[R].AIAA-2000-1023, 2000.
[9]	彭云晖, 林宇震, 刘高恩.三旋流器燃烧室出口温度分布的初步试验研究[J].航空动力学报, 2007, 22(4):554-558. PENG Yunhui, LIN Yuzhen, LIU Gaoen.A preliminary experimental study of pattern factor for a triple swirler combustor[J].Journal of Aerospace Power, 2007, 22(4):554-558.(in Chinese)
[10]	宁榥, 高歌.燃烧室气动力学[M].北京:科学出版社, 1987.
[11]	Mongia H C.Engineering aspects of complex gas turbine combustion mixers:Part Ⅰ high ΔT[R].AIAA-2011-107, 2011.
[12]	LI Guoqiang, Gutmark E J.Flow field measurement of triple swirler spray combustor[R].AIAA-2002-4010, 2002.
[13]	LI Guoqiang, Gutmark E J.Combustion characteristics of a multiple swirl spray combustor[R].AIAA-2003-0489, 2003.
[14]	Zheng Q P, Jasuja A K, Lefebvre A H.Structure of air blast sprays under high ambient pressure conditions[J].Journal of Engineering for Gas Turbines and Power, 1997, 119(3):512-518.
[15]	Jasuja A K, Tam C K.Determination of air blast atomized spray structure using state-of-the-art laser diagnostics[R].AIAA 92-3232, 1992.
[16]	袁怡祥, 林宇震, 刘高恩.旋流杯燃烧室头部流场与喷雾对贫油熄火的影响[J].航空动力学报, 2004, 19(3):332-336. YUAN Yixiang, LIN Yuzhen, LIU Gaoen.The effect of flow field and fuel spray of combustor with swirl cup on lean blowout limit at idle condition[J].Journal of Aerospace Power, 2004, 19(3):332-336.(in Chinese)
[17]	《航空发动机设计手册》总编委会.航空发动机设计手册:第9分册主燃烧室[M].北京:航空工业出版社, 2000.
[18]	Mohammad B S, Jeng S M.Design procedures and a developed computer code for preliminary single annular combustor design[R].AIAA-2009-5208, 2009.
[19]	Hsiao G, Mongia H C.Swirl cup modeling:Part Ⅲ grid independent solution with different turbulence models[R].AIAA-2003-1349, 2003.