基于PIV技术对三级旋流杯燃烧室流场的测量

王成军; 江平; 辛欣; 陈保东; 陈科华

doi:10.13224/j.cnki.jasp.2015.05.002

基于PIV技术对三级旋流杯燃烧室流场的测量

doi: 10.13224/j.cnki.jasp.2015.05.002

沈阳航空航天大学航空航天工程学部, 沈阳 110136

基金项目:

国家自然科学基金(51476106)

详细信息

作者简介:
王成军(1967-),男,辽宁沈阳人,副教授,博士,主要从事航空发动机燃烧技术的研究.

中图分类号: V231.2⁺3
计量
- 文章访问数: 1367
- HTML浏览量: 5
- PDF量: 1019
- 被引次数: 0
出版历程
- 收稿日期: 2013-12-19
- 刊出日期: 2015-05-28

Measurement of triple-stage swirler cup combustor flow field based on PIV technology

Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China

摘要

摘要: 参照单级旋流器设计方法,设计4种三级旋流杯中不同叶片数和叶片安装角第三级旋流器,采用particle image velocity(PIV)技术对三级旋流杯燃烧室流场进行研究.研究结果表明:随着第三级旋流器叶片安装角和叶片数的增加,主燃区的轴向速度逐渐变小,使得主燃孔射流作用增强;在同样叶片数情况下,增大第三级旋流器叶片安装角,使旋流强度增强;对于第三级旋流器不同安装角、第三级旋流器叶片数增加都使轴向速度变化趋于平缓,使燃烧室内主流受主燃孔射流扰动影响较小,流动更平缓.
- 航空发动机 /
- 燃烧室 /
- 三级旋流杯 /
- 粒子成像速度仪 /
- 流场
Abstract: With reference to single-stage swirler design method, four kinds of third stage swirler of different blade numbers and installation angles in triple-stage swirler cup were designed. Triple-stage swirler cup combustor flow field was studied through the particle image velocity(PIV) technology. The experimental results show that with the increase of the third stage swirler blade number and installation angle, the axial velocity in main combustion zone decreases gradually, enhancing the effect of main combustion hole jet. Under the same blade number condition, the third stage swirler vortex intensity is boosted with the increase of the third stage swirle blade installation angle. For different third stage swirler blade installation angles, the flat trend of axial velocity increases with the increase of the third stage swirler blade number, making the effect of combustor flow disturbance decreases by main combustion hole jet and the mainstream flow more smoothly.
- aero-engine /
- combustor /
- triple-stage swirler cup /
- particle image velocity /
- flow field

HTML

参考文献(18)

[1]	Bahr D W.Technology for the design of high temperture rise combustor[R].AIAA 85-1292, 1985.
[2]	胡正义.航空发动机设计手册[M].北京:航空工业出版社, 2000.
[3]	Kastl J A, Herberling P V, Matulatis J M.Low NOx combustor development[R].NASA/CR-2005-213326, 2005.
[4]	Wang H Y, McDonell V G, Samuelsen G S.Influence of hardware design on the flow field structures and the patterns of droplet dispersion:Part Ⅰ mean quantities[J].Journal of Engineering for Gas Turbines and Power, 1995, 117(2):282-289.
[5]	Ateshkadi A, McDonell V G, Samuelsen G S.Effect of mixer geometry on fuel spray distribution, emission and stability[R].AIAA 98-0247, 1998.
[6]	Wang H Y, McDonell V G, Sowa W A.Scaling of the two phase flow downstream of a gas turbine combustor swirl cup:Part Ⅰ mean quantities[J].Journal of Engineering for Gas Turbines and Power, 1993, 115(3):453-460.
[7]	Wang H Y, McDonell V G, Samuelsen G S.The influence of spray angle on the continuous and discrete phase flow field downstream in an engine combustor swirl cup[R].AIAA 92-3231, 1992.
[8]	Li G, Gutmark E J.Combustion characteristics of a multiple swirl spray combustor[R].AIAA-2003-0489, 2003.
[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 operattion stability range[J].Journal of Aerospace Power, 2004, 19(1):142-147.(in Chinese)
[10]	林宇震, 刘高恩, 王华芳.反向与同向双旋流器流场的试验研究[J].航空动力学报, 1995, 10(4):108-110. LIN Yuzhen, LIU Gaoen, WANG Huafang.Experimental study of the opposite and same dual-stage swirler flow distribution[J].Journal of Aerospace Power, 1995, 10(4):108-110.(in Chinese)
[11]	刘伟, 林宇震, 刘高恩.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.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)
[12]	袁怡祥, 林宇震, 刘高恩.旋流杯燃烧室头部流与喷雾对贫油熄火的影响[J].航空动力学报, 2004, 19(3):332-337. 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):332-337.(in Chinese)
[13]	吴振宇.带有三级旋流器燃烧室的数值研究[D].沈阳:沈阳航空航天大学, 2010. WU Zhenyu.Numerical study of combustion with triple swirlers[D].Shenyang:Shenyang Aerospace University, 2010.(in Chinese)
[14]	范洁川.近代流动显示技术[M].北京:国防工业出版社, 2002.
[15]	Lefebvre A H.Gas turbine combustion[M].London:Taylor & Francis Press, 1999.
[16]	党新宪, 赵坚行, 吉洪湖.试验研究双旋流头部燃烧室几何参数对燃烧性能的研究[J].航空动力学报, 2007, 22(10):1640-1645. DANG Xinxian, ZHAO Jianxing, JI Honghu.Experimental study of effects of geometric parameters on combustion performance of dual-stage swirler combustor[J].Journal of Aerospace Power, 2007, 22(10):1640-1645.(in Chinese)
[17]	焦树建.径向旋流器的设计方法及其燃烧特[J].燃气轮机技术, 1994, 7(4):33-42. JIAO Shujian.Design method and combustion character of radial swirler[J].Gas Turbine Technology, 1994, 7(4):33-42.(in Chinese)
[18]	Grinstein F F, Young T R, Li G.Computational and experimental analysis of the flow dynamics in a multi-swirler combustor[R].AIAA-2002-1006, 2002.