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回流燃烧室流动特性试验

翟维阔 胡阁

翟维阔, 胡阁. 回流燃烧室流动特性试验[J]. 航空动力学报, 2019, 34(10): 2081-2090. doi: 10.13224/j.cnki.jasp.2019.10.001
引用本文: 翟维阔, 胡阁. 回流燃烧室流动特性试验[J]. 航空动力学报, 2019, 34(10): 2081-2090. doi: 10.13224/j.cnki.jasp.2019.10.001
ZHAI Weikuo, HU Ge. Experiment on flow characteristics of a reverse-flow combustor[J]. Journal of Aerospace Power, 2019, 34(10): 2081-2090. doi: 10.13224/j.cnki.jasp.2019.10.001
Citation: ZHAI Weikuo, HU Ge. Experiment on flow characteristics of a reverse-flow combustor[J]. Journal of Aerospace Power, 2019, 34(10): 2081-2090. doi: 10.13224/j.cnki.jasp.2019.10.001

回流燃烧室流动特性试验

doi: 10.13224/j.cnki.jasp.2019.10.001

Experiment on flow characteristics of a reverse-flow combustor

  • 摘要: 为了揭示有/无燃烧状态下燃烧室热态和冷态流场的特征和流动特性,针对某型回流燃烧室单头部试验件,使用粒子图像测速仪(PIV),测量燃烧室燃烧状态下不同截面处的热态流场,以及没有燃烧状态下不同截面处的冷态流场,探讨不同总压损失系数对回流燃烧室热态/冷态流场特征及流动特性的影响。研究表明:随着总压损失系数的增大,冷态条件下各截面流场结构基本保持不变,如射流孔穿透深度、射流角度、回流区位置及大小、流线等基本保持一致,但是各位置点速度大小逐渐增大。热态条件下各截面流场随着总压损失系数增大,流场结构也基本保持不变;相同总压损失系数时,热态流场与冷态流场存在差异,燃油喷射与气流的相对运动将会对燃烧室头部的流场结构造成影响,速度较冷态流动时略微增大。

     

  • [1] MONGIA H C.Engineering aspects of complex gas turbine combustion mixers:Part Ⅰ high ΔT[R].AIAA-2011-107,2011.
    [2] MELLOR A M.Design of modern turbine combustors[M].London:Academic Press,1990.
    [3] 林阳,林宇震,刘高恩.收口套筒主燃区流场的PIV测量[J].航空动力学报,2007,22(12):1989-1993.LIN Yang,LIN Yuzhen,LIU Gaoen.PIV experimental study of primary zone flow field of convergent sleeve[J].Journal of Aerospace Power,2007,22(12):1989-1993.(in Chinese)
    [4] 杨浩林,赵黛青,杨卫斌.扩散燃烧流场的PIV测试方法探讨[J].工程热物理学报,2007,28(增刊2):233-236.YANG Haolin,ZHAO Daiqing,YANG Weibin.Application of PIV system to the diffusion combustion flow field[J].Journal of Engineering Thermophysics,2007,28(Suppl.2):233-236.(in Chinese)
    [5] 于锦峰,郭志辉,张军峰,等.套筒长度对火焰筒流场和雾化特性的影响[J].航空动力学报,2009,24(11):2506-2513.YU Jinfeng,GUO Zhihui,ZHANG Junfeng,et al.Experimental study the effect of flare sleeve length on the flow field and spray characterization of a combustor swirl cup[J].Journal of Aerospace Power,2009,24(11):2506-2513.(in Chinese)
    [6] YAN Yingwen,LI Jinghua,XU Rong,et al.PIV Measurement for swirler flow field in gas turine combustor[J].Transactions of Nanjing University of Aeronautics and Astronautics,2012,29(4):307-317.
    [7] HUANG R F,TSAI F C.Flow field characteristics of swirling double concentric jets[J].Experimental Thermal and Fluid Science,2001,25(3/4):151-161.
    [8] BLUNCK D L,SHOUSE D T,NEUROTH C,et al.Experimental studies of cavity and core flow interactions with application to ultra-compact combustors[J].Journal of Engineering for Gas Turbines and Power,2014,136(9):091505.1-091505.8.
    [9] REDDY K S,REDDY D N,VARAPRASAD C M.Experimental and numerical investigations of swirling flows in a reverse flow gas turbine combustor[R].AIAA 2007-4219,2007.
    [10] BHARANI S,SINGH S N,AGRAWAL D P.Effect of swirl on the flow characteristics in the outer annulus of a prototype reverse-flow gas turbine combustor[J].Experimental Thermal and Fluid Science,2001,25(6):337-347.
    [11] 赵硕,黄章芳,成胜军.进气对某回流燃烧室性能影响的试验[J].航空动力学报,2015,30(6):1293-1297.ZHAO Shuo,HUANG Zhangfang,CHENG Shengjun.Experiment on effect of inlet airflow on performance of a reverse-flow combustor[J].Journal of Aerospace Power,2015,30(6):1293-1297.(in Chinese)
    [12] 梁志鹏,林宇震,许全宏,等.进口流场畸变对回流燃烧室出口温度分布的影响[J].航空动力学报,2016,31(5):1142-1148.LIANG Zhipeng,LIN Yuzhen,XU Quanhong,et al.Effects of inlet velocity distortion on outlet temperature distribution of a reverse-flow combustor[J].Journal of Aerospace Power,2016,31(5):1142-1148.(in Chinese)
    [13] VASHAHI F,LEE S,LEE J.Experimental analysis of the swirling flow in a model rectangular gas turbine combustor[J].Experimental Thermal and Fluid Science,2016,76:287-295.
    [14] CHEN Fang,LIU Hong,Partical image velocimetry for combustion measurements:applications and developments[J].Chinese Journal of Aeronautics,2018,31(7):1407-1427.
    [15] LI G,GUTMARK E.Effect of exhaust nozzle geometry on combustor flow field and combustion characteristics[J].Proceedings of the Combustion Institute,2005,30(2):2893-2901.
    [16] DHANUKA S K,DRISCOLL J F,MONGIA H C.Instantaneous flow structures in a reacting gas turbine combustor[R].AIAA-2008-4683,2008.
    [17] MOHAMMAD B,JENG S M,ANDAC M G.Influence of the primary jets and fuel injection on the aerodynamics of prototype annular gas turbine combustor sector[J].Journal of Engineering for Gas Turbines and Power,2011,133(1):011505.1-011505.8.
    [18] CHONG C T,HOCHGREB S.Flow field of a model gas turbine swirl burner[J].Advanced Materials Research,2012,622/623:1119-1124.
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出版历程
  • 收稿日期:  2019-01-23
  • 刊出日期:  2019-10-28

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