三级轴向旋流器影响燃烧室性能的试验

丁国玉; 何小民; 赵自强; 朱志新; 葛佳伟

doi:10.13224/j.cnki.jasp.2015.03.020

三级轴向旋流器影响燃烧室性能的试验

doi: 10.13224/j.cnki.jasp.2015.03.020

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: 2013-09-18
- 刊出日期: 2015-03-28

Experiment on effect of triple axial swirler on combustor performance

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: 对装有4种不同三级轴向旋流器的燃烧室开展了常压下不同进口速度、进口温度和油气比状态下的燃烧室性能试验研究,获得了不同三级轴向旋流器燃烧室的流阻性能和燃烧性能.研究结果表明:各方案中三级轴向旋流器燃烧室的总压损失系数均随着进口速度的增大(由40m/s增加到70m/s)而增加;进口温度的升高对点火和熄火均有利;旋向组合为顺时针—逆时针—顺时针的三级轴向旋流器燃烧室性能与旋向组合为逆时针—逆时针—顺时针的三级轴向旋流器燃烧室燃烧性能相比,总压损失系数稍大、贫油熄火性能较优、燃烧效率稍低;内旋流器空气流量的减少可使得三级轴向旋流器燃烧室的总压损失系数增大、贫油熄火油气比和燃烧效率均有所降低.
- 三级轴向旋流器 /
- 燃烧室 /
- 贫油熄火 /
- 旋向组合 /
- 研究参数
Abstract: Experiments were conducted to study four different triple axial swirlers combustor about flow drag performance and combustion performance of a triple axial swirler combustor at different inlet airflow velocities, inlet airflow temperatures and fuel-air ratios with fixed atmospheric pressure. The test results show that: the total pressure loss coefficient of triple axial swirler combustor increases with inlet airflow velocity increasing (from 40m/s to 70m/s), and inlet airflow temperature rise is helpful to ignition and lean blowout; by comparing the combustion performance of the triple axial swirler combustor of "clockwise—counterclockwise—clockwise"rotational direction combinations with the combustor of "counterclockwise—counterclockwise—clockwise" rotational direction combination, the total pressure loss coefficient is a little higher and the lean blowout performance is better, while the combustion efficiency is a little lower; decreasing the inner swirler airflow rate would lead to increase of total pressure loss coefficient, and decline of lean blowout fuel-air ratio and combustion efficiency.
- triple axial swirler /
- combustor /
- lean blowout /
- rotating direction combination /
- research parameters

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参考文献(16)

[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]	Bahr D W.Technology for the design of high temperature rise combustors[R].AIAA 85-1292,1985.
[3]	Mongia H C.Engineering aspects of complex gas turbine combustion mixers:Part Ⅰ high ΔT[R].AIAA-2011-107,2011.
[4]	LI Guoqiang,Gutmark E J.Flow field measurement of triple swirler spray combustor[R].AIAA-2002-4010,2002.
[5]	LI Guoqiang,Gutmark E J.Combustion characteristics of a multiple swirl spray combustor[R].AIAA-2003-0489,2003.
[6]	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.
[7]	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.
[8]	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)
[9]	袁怡祥,林宇震,刘高恩.三旋流器头部燃烧室拓宽燃烧稳定工作范围的研究[J].航空动力学报,2004,19(1):142-147. YUAN Yixiang,LIN Yuzhen,LIU Gaoen.Combustor dome design with three swirlers for widening the operation stability range[J].Journal of Aerospace Power,2004,19(1):142-147.(in Chinese)
[10]	LI Guoqiang,Gutmark E J.Experimental and numerical studies of the velocity field of a triple annular swirler[R].ASME Paper GT-2002-30069,2002.
[11]	LI Guoqiang,Angier S,Lambolez O,et al.Experimental study of velocity flow field for a multiple swirl spray combustor[R].AIAA-2002-0618,2002.
[12]	吴治永,林宇震,刘高恩,等.基于CFD分析改进三旋流燃烧室头部设计[J].推进技术,2009,30(5):533-537. WU Zhiyong,LIN Yuzhen,LIU Gaoen,et al.Dome structure modification of a high temperature rise combustor based on CFD simulation[J].Journal of Propulsion Technology,2009,30(5):533-537.(in Chinese)
[13]	刘伟,林宇震,刘高恩,等.低压条件下复合式多级旋流杯燃烧室燃烧效率研究[J].航空动力学报,2004,19(5):650-655. LIU Wei,LIN Yuzhen,LIU Gaoen,et al.Research of combustion efficiency of combustors using hybrid airblast atomizer under low pressure[J].Journal of Aerospace Power,2004,19(5):650-655.(in Chinese)
[14]	宁榥,高歌.燃烧室气动力学[M].北京:科学出版社,1987.
[15]	《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.
[16]	Mohammad B S,Jeng S M.Design procedures and a developed computer code for preliminary single annular combustor design[R].AIAA-2009-5208,2009.