Volume 36 Issue 9
Sep.  2021
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2021  >  36(9): 1932-1941
TAN Yunchuan, ZHONG Huagui, SUN Ruili, SUN Haitao. Effect of lean blowout performance of trapped vortex combustor of the afterburner[J]. Journal of Aerospace Power, 2021, 36(9): 1932-1941. doi: 10.13224/j.cnki.jasp.20210121
Citation: TAN Yunchuan, ZHONG Huagui, SUN Ruili, SUN Haitao. Effect of lean blowout performance of trapped vortex combustor of the afterburner[J]. Journal of Aerospace Power, 2021, 36(9): 1932-1941. doi: 10.13224/j.cnki.jasp.20210121
shu

Effect of lean blowout performance of trapped vortex combustor of the afterburner

doi: 10.13224/j.cnki.jasp.20210121

  • Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Mianyang Sichuan 621300，China

  • Received Date: 2021-03-17
  • Publish Date: 2021-09-28
    Abstract
  • Three different schemes of cavity structure were designed to study the lean blowout （LBO） performance by test research method.Aviation kerosene was employed as fuel.In all operating conditions，the inlet pressure ratio of out and inner bypass varied from 0.97-1.07 and the mainstream Mach number ranged from 0.13-0.20.It was revealed that the fuel air ratio of lean blowout increased with the increasing inlet pressure ratio of out and inner bypass.LBO also increased with the increasing mainstream Mach number，and when the mainstream Mach number was larger，the increase was larger.In upper region of the vortex，the axial average of absolute velocity decreased，and the positon of the main vortex center was closer to the after wall of the cavity within a certain range，and the lean blowout performance of trapped vortex combustor of the afterburner was excellent.

     

    • FullText(HTML)
  • loading
    • References(20)
  • [1]
    HSU K Y,GOSS L P,TRUMP D D，et al.Performance of a trapped-vortex combustor[R].AIAA-95-0810,1995.
    [2]
    CHRISTOPHER S，SURESH M.Simulation of fuel-air mixing and combustion in a trapped-vortex combustor[R].AIAA 2000-0478,2000.
    [3]
    KATTA V R，ROQUMORE W M.Study on trapped vortex combustor-efect of injection on dynamics of non-reacting and reacting flows in a cavity[R].AIAA-97-3256，1997.
    [4]
    KATTA V R，ROQUMORE W M.Study on trapped-vortex combustor-effect of injection on flow dynamics[J].Journal of Propulsion and Power，1998，14（3）：273-281.
    [5]
    KATTA V R，ROQUMORE W M.Numerical study on trapped-vortex combustor concepts for stable combustion[J].Transactions of the ASME,1998，120（3）：60-68.
    [6]
    何小民,王家骅.驻涡火焰稳定器冷态流场特性的初步研究[J].航空动力学报,2002,17（5）:567-571.
    [7]
    何小民,许金生,苏俊卿.驻涡区进口结构参数影响TVC燃烧性能的试验[J].航空动力学报,2007,22（11）:1798-1802.
    [8]
    李瑞明,刘玉英,刘河霞,等.驻涡燃烧室主流对凹腔涡流动的影响[J].航空动力学报,2009,24（7）:1482-1487.
    [9]
    邢菲,樊未军,柳杨,等.凹腔油气匹配对驻涡燃烧室点火性能影响试验[J].推进技术,2008,29（4）:30-34,39.
    [10]
    吴泽俊,何小民,洪亮,等.采用离心喷嘴的单凹腔驻涡燃烧室点火与贫熄特性[J].推进技术,2015,36（4）:601-607.
    [11]
    朱一骁,何小民,叶正源,等.可变几何单凹腔驻涡燃烧室的贫油熄火性能试验[J].推进技术,2018,39（6）:1347-1353.
    [12]
    汤彬,邢菲,邹建锋,等.驻涡燃烧室凹腔温度变化规律及气量分配[J].推进技术,2011,32（2）:182-187.
    [13]
    何小民,姚锋.流动和油气参数对驻涡燃烧室燃烧性能的影响[J].航空动力学报,2006,21（5）:810-813.
    [14]
    樊未军,易琪,严明,等.驻涡燃烧室凹腔双涡结构研究[J].中国电机工程学报,2006,26（9）:66-70.
    [15]
    STURGESS G J，SHOUSE D T，ZELINA J.Emissions reduction technologies for military gas turbine engines[R].AIAA 2003-2622,2003.
    [16]
    邢菲,孟祥泰,李继保,等.凹腔双驻涡稳焰冷态流场初步研究[J].推进技术,2008,29（2）:135-138.
    [17]
    金义,何小民,彭春梅,等.驻涡燃烧室驻涡区三维冷态流动特性数值研究[J].南京航空航天大学学报,2014,46（2）:272-279.
    [18]
    李瑞明，刘玉英，马文杰，等.驻涡燃烧室掺混孔对流量分配及燃烧性能的影响[J] .航空动力学报,2010,25（3）:488-495.
    [19]
    何小民，许金生，苏俊卿，等.驻涡燃烧室燃烧性能试验[J].航空动力学报,2009,24（2）:318-323.
    [20]
    金如山.航空燃气轮机燃烧室[M].北京：宇航出版社，1988：129-147.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2426.0KB)
    XML

    Article Metrics

    Article views (412) PDF downloads(142) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return