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变循环发动机模态转换的几何调节规律

周红 王占学 张晓博 张明阳

周红, 王占学, 张晓博, 张明阳. 变循环发动机模态转换的几何调节规律[J]. 航空动力学报, 2015, 30(9): 2160-2166. doi: 10.13224/j.cnki.jasp.2015.09.014
引用本文: 周红, 王占学, 张晓博, 张明阳. 变循环发动机模态转换的几何调节规律[J]. 航空动力学报, 2015, 30(9): 2160-2166. doi: 10.13224/j.cnki.jasp.2015.09.014
ZHOU Hong, WANG Zhan-xue, ZHANG Xiao-bo, ZHANG Ming-yang. Geometry regulating law of variable cycle engine during mode transition[J]. Journal of Aerospace Power, 2015, 30(9): 2160-2166. doi: 10.13224/j.cnki.jasp.2015.09.014
Citation: ZHOU Hong, WANG Zhan-xue, ZHANG Xiao-bo, ZHANG Ming-yang. Geometry regulating law of variable cycle engine during mode transition[J]. Journal of Aerospace Power, 2015, 30(9): 2160-2166. doi: 10.13224/j.cnki.jasp.2015.09.014

变循环发动机模态转换的几何调节规律

doi: 10.13224/j.cnki.jasp.2015.09.014
详细信息
    作者简介:

    周红(1988-),女,湖北荆州人,博士生,主要从事航空发动机总体设计研究.

  • 中图分类号: V235.16;TP301.6

Geometry regulating law of variable cycle engine during mode transition

  • 摘要: 考虑了变循环发动机转子惯性效应和部件容积效应,分析了模态选择阀门面积、核心驱动风扇级导叶角度、低压涡轮导向器面积、喷管喉部面积等几何参数及其不同组合调节方式对变循环发动机模态转换过程的影响,并与实验数据进行了对比.结果表明:所建立的数学模型能正确反映变循环发动机在模态转换过程中参数的变化规律.为确保转换过程的顺利进行,在放大(关小)模态选择阀门面积时,应关小(放大)核心驱动风扇级导叶角度.低压涡轮导向器面积和喷管喉部面积的调节可使得转换过程中参数的变化更加平稳.

     

  • [1] Allan R D.General Electric Company variable cycle engine technology demonstrator program[R].AIAA 79-1311,1979.
    [2] Dabney T R.Anser.Engine wars:competition for US fighter engine production[R].AIAA 98-3115,1998.
    [3] Simmons R J.Design and control of a variable geometry turbofan with an independently modulated third stream[D].Ohio:Ohio State University,2009.
    [4] Welge H R,Bonet J,Magee T,et al.N+3 advanced concept studies for supersonic commercial transport aircraft entering service in the 2030-2035 period[R].NASA CR-217084,2011.
    [5] French M W,Allen G L.NASA VCE test bed engine aerodynamic performance characteristics and test results[R].AIAA 81-1594,1981.
    [6] 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.
    [7] Sullivan T J,Parker D E.Design study and performance analysis of a high-speed multistage variable-geometry fan for a variable cycle engine[R].NASA CR-159545,1979.
    [8] Hurtle J E,Toot P D,Wanger R P.Full authority digital electronic control (FADEC):variable cycle engine demonstration[R].AIAA 81-1498,1981.
    [9] Rock S M,De Hoff R L.Variable cycle engine multivariable control synthesis interim report:control structure definition[R].AFAPL-TR-79-2043,1979.
    [10] Przybylko S J,Rock S M.Evaluation of a multivariable control design on a variable cycle engine simulation[R].AIAA 82-1077,1982.
    [11] 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)
    [12] 刘增文,王占学,蔡元虎,等.变循环发动机模态转换数值模拟[J].航空动力学报,2011,26(9):2128-2132. LIU Zengwen,WANG Zhanxue,CAI Yuanhu,et al.Numerical simulation on bypass transition of variable cycle engines[J].Journal of Aerospace Power,2011,26(9):2128-2132.(in Chinese)
    [13] 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)
    [14] 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)
    [15] Corbett M,Wolff J M.Modeling transient effects of a double bypass engine[R].AIAA-2010-7090,2010.
    [16] 樊思齐,徐芸华.航空推进系统控制[M].西安:西北工业大学出版社,1995:34-44.
    [17] Sellers J F,Daniele C J.DYNGEN-A program for calculating steady-state and transient performance of turbojet and turbofan engines[R].NASA TN D-7901,1975.
    [18] Franciscus L.Interim computer program for estimating aircraft engine weight and dimensions on a component basis[R].NASA TM X-73404,1976.
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出版历程
  • 收稿日期:  2015-04-21
  • 刊出日期:  2015-09-28

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