| 基于PIV技术对三级旋流杯燃烧室流场的测量 |
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| 引用本文： | 王成军,江平,辛欣,陈保东,陈科华.基于PIV技术对三级旋流杯燃烧室流场的测量[J].航空动力学报,2015,30(5):1032-1039. |
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| 作者姓名： | 王成军 江平 辛欣 陈保东 陈科华 |
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| 作者单位： | 沈阳航空航天大学航空航天工程学部,沈阳,110136 |
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| 基金项目： | 国家自然科学基金(51476106) |
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| 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.
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| 关 键 词： | 航空发动机 燃烧室 三级旋流杯 粒子成像速度仪 流场 |
| 收稿时间： | 2013/12/19 0:00:00 |
Measurement of triple-stage swirler cup combustor flow field based on PIV technology |
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| WANG Cheng-jun,JIANG Ping,XIN Xin,CHEN Bao-dong and CHEN Ke-hua.Measurement of triple-stage swirler cup combustor flow field based on PIV technology[J].Journal of Aerospace Power,2015,30(5):1032-1039. |
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| Authors: | WANG Cheng-jun JIANG Ping XIN Xin CHEN Bao-dong and CHEN Ke-hua |
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| Institution: | Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China,Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China,Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China,Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China and Faculty of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, China |
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| 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. |
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| Keywords: | aero-engine combustor triple-stage swirler cup particle image velocity flow field |
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