Volume 31 Issue 12
Dec.  2016
Turn off MathJax
Article Contents
ZHOU Hong, WANG Zhan-xue, LIU Zeng-wen, ZHANG Ming-yang. Impact of variable area bypass injector on variable cycle engine performance[J]. Journal of Aerospace Power, 2016, 31(12): 2842-2850. doi: 10.13224/j.cnki.jasp.2016.12.004
Citation: ZHOU Hong, WANG Zhan-xue, LIU Zeng-wen, ZHANG Ming-yang. Impact of variable area bypass injector on variable cycle engine performance[J]. Journal of Aerospace Power, 2016, 31(12): 2842-2850. doi: 10.13224/j.cnki.jasp.2016.12.004

Impact of variable area bypass injector on variable cycle engine performance

doi: 10.13224/j.cnki.jasp.2016.12.004
  • Received Date: 2015-03-31
  • Publish Date: 2016-12-28
  • The geometry regulating laws of forward and rear bypass injectors of variable cycle engine were analyzed. A mathematic model capable of calculating the variable cycle engine steady and transition performance was established. It considered the local total pressure loss caused by sudden area change at forward bypass injector and mode selector valve. The impacts of geometry regulating laws of forward and rear bypass injectors on variable cycle engine performance and stability were simulated with single bypass mode, double bypass mode and mode transitioning, and the simulation results were compared with NASA test data. The results indicate the opening of forward bypass injector's inner bypass area can decrease recirculation margin and increase fan and core drive fan stage surge margin in single bypass mode. During the late period of transforming from single into double bypass mode, the reduction of fan pressure ratio will diminish by closing rear bypass injector's outer bypass area. It's suggested that the forward bypass injector's inner bypass area should be changed, and the total area should be kept unchanged, while the rear bypass injector's outer bypass area should be changed, and the inner bypass area should be kept unchanged.

     

  • loading
  • [1]
    Kurzke J.The mission define the cycle:turbojet,turbofan and variable cycle engine for high speed propulsion[R].NATO OTAN RTO-EN-AVT-185,2010.
    [2]
    Krebs J N,Allan R D.Supersonic propulsion 1970-1977[R].AIAA 77-832,1977.
    [3]
    Vdoviak J W,Ebacher J A.VCE test bed engine for supersonic cruise research[R].NASA CP-2108,1979.
    [4]
    French M W,Allen G L.NASA VCE test bed engine aerodynamic performance characteristics and test results[R].AIAA 81-1594,1981.
    [5]
    Allan R D.General Electric Company variable cycle engine technology demonstrator program[R].AIAA 79-1311,1979.
    [6]
    唐海龙.面向对象的航空发动机性能仿真系统及其应用[D].北京:北京航空航天大学,2000. TANG Hailong.Object-oriented aeroengine performance simulation system and its application[D].Beijing:Beijing University of Aeronautics and Astronautics,2000.(in Chinese)
    [7]
    苟学中,周文祥,黄金泉.变循环发动机部件级建模技术[J].航空动力学报,2013,28(1):104-111. GOU Xuezhong,ZHOU Wenxiang,HUANG Jinquan.Component-level modeling technology for variable cycle engine[J].Journal of Aerospace Power,2013,28(1):104-111.(in Chinese)
    [8]
    王元,张平平,李秋红,等.变循环发动机建模方法研究及验证[J].航空动力学报,2014,29(11):2643-2651. WANG Yuan,ZHANG Pingping,LI Qiuhong,et al.Variable cycle engine modeling method research and validation[J].Journal of Aerospace Power,2014,29(11):2643-2651.(in Chinese)
    [9]
    周红,王占学,刘增文,等.双外涵变循环发动机可变几何特性研究[J].航空学报,2014,35(8):2126-2135. ZHOU Hong,WANG Zhanxue,LIU Zengwen,et al.Variable geometry characteristics research of double bypass variable cycle engine[J].Acta Aeronautica et Astronautica Sinica,2014,35(8):2126-2135.(in Chinese)
    [10]
    Allan R D,Joy W.Advanced supersonic propulsion system technology study:Phases Ⅲ and Ⅳ varible cycle engine[R].NASA CR-135236,1977.
    [11]
    Simmons R J.Variable cycle engine with split fan section:US,4068471[P].1978-01-17.
    [12]
    Conrad D W,Guy K F.Individual bypass injector valves for a double bypass variable cycle turbofan engine:US,4175384[P].1979-10-27.
    [13]
    John W V,Donald P M.Variable slot bypass injector:US,5694767[P].1997-11-09.
    [14]
    Vdoviak J W,Knott P R,Ebacker J J.Aerodynamic/acoustic performance of YJ101/ double bypass VCE with coannular plug nozzle[R].NASA CR-159869,1981.
    [15]
    法罗基.飞机推进[M].刘洪,陈方,杜朝辉,译.上海:上海交通大学出版社,2010.
    [16]
    Kurzke J.GasTurb 11:design and off-design performance of gas turbines[R].Friedrichshafen,Germany:MTU Company,2007.
    [17]
    Franciscus L.Interim computer program for estimating aircraft engine weight and dimensions on a component basis[R].NASA TM-73404,1976.
  • 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

    Article Metrics

    Article views (1755) PDF downloads(749) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return