Volume 29 Issue 10
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CHENG Ming, LIN Hong-jun, LI Feng. Effect of swirl cup design parameters on combustion performance[J]. Journal of Aerospace Power, 2014, (10): 2355-2361. doi: 10.13224/j.cnki.jasp.2014.10.011
Citation: CHENG Ming, LIN Hong-jun, LI Feng. Effect of swirl cup design parameters on combustion performance[J]. Journal of Aerospace Power, 2014, (10): 2355-2361. doi: 10.13224/j.cnki.jasp.2014.10.011
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Effect of swirl cup design parameters on combustion performance

doi: 10.13224/j.cnki.jasp.2014.10.011

  • 1. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;

  • 2. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 2013-10-21
  • Publish Date: 2014-10-28
    Abstract
  • Based on the three-dimensional numerical simulation and rig test,the effect of swirl cup's design parameters of head of flame tube, such as the relative flow rate and the swirl number of secondary swirler, on combustion performance of an aero-engine main combustor was researched. The researched performance includes the outlet temperature field distribution and nitrogen oxides (NOx) emissions.It is shown that the result of numerical simulation and rig test is consistent: with the increase of the secondary swirler's relative flow rate,the outlet temperature field of the main combustor deteriorates, and the nitrogen oxides emission slightly reduces;with the deviation of swirl number of the secondary swirler from the benchmark design value, the outlet temperature field deteriorates, while nitrogen oxides emission increases with the increase of swirl number.

     

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    • References(15)
  • [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]
    金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1988.
    [3]
    候晓春,季鹤鸣,刘庆国,等.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002.
    [4]
    方昌德.世界航空发动机手册[M].北京:航空工业出版社,1996.
    [5]
    Gupta A K,Lilley D G,Syred N.Swirl flows[M].Kent:Abaus Press,1984.
    [6]
    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.An investigation of air flow field produced by a double-swirler airblast atomizer[J].Journal of Aerospace Power,1995,10(4):108-110.(in Chinese)
    [7]
    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.
    [8]
    Ateshkadi A,McDonell V G,Samuelsen G S.Effect of mixer geometry on fuel spray distribution,emission and stability[R].AIAA 98-0247,1998.
    [9]
    Wang H Y,McDonell V G,Sowa W A,et al.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(2):453-460.
    [10]
    Wang H Y,McDonell V G,Samuelsen G S.Correlation on droplet behavior with gas 2 phase structures in a gas turbine combustor[R].AIAA 93-1767,1993.
    [11]
    Woo S S,Yeoung M H,Dae S L.Flow and spray characteristics of a lean fuel injection module with radial swirlers[R].ASME Paper 2000-GT2118,2000.
    [12]
    Woodmansee M A,Ball I C,Barlow K W.Experimental flow field characterization of a combustor swirl cup[R].AIAA-2002-2864,2002.
    [13]
    Fluent Inc.FLUENT 6.1 User's Guide[M].New York:Fluent Inc,2003.
    [14]
    Nickolaus D,Smith C E.CFD modeling of a gas turbine combustor from compressor exit to inlet[J].Journal of Engineering for Gas Turbines and Power,2003,121(1):89-95.
    [15]
    程明,尚守堂,李锋.主燃烧室全流动域三维数值计算和性能分析[R].沈阳:中国航空学会动力分会燃烧与传热传质学术会议,2007.
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