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涵道比调节对核心机驱动风扇级与高压压气机匹配性能影响

马昌友 侯敏杰 幸晓龙

马昌友, 侯敏杰, 幸晓龙. 涵道比调节对核心机驱动风扇级与高压压气机匹配性能影响[J]. 航空动力学报, 2018, 33(2): 392-401. doi: 10.13224/j.cnki.jasp.2018.02.017
引用本文: 马昌友, 侯敏杰, 幸晓龙. 涵道比调节对核心机驱动风扇级与高压压气机匹配性能影响[J]. 航空动力学报, 2018, 33(2): 392-401. doi: 10.13224/j.cnki.jasp.2018.02.017
Effects of bypass ratio on the matching performance between core driven fan stage and high pressure compressor[J]. Journal of Aerospace Power, 2018, 33(2): 392-401. doi: 10.13224/j.cnki.jasp.2018.02.017
Citation: Effects of bypass ratio on the matching performance between core driven fan stage and high pressure compressor[J]. Journal of Aerospace Power, 2018, 33(2): 392-401. doi: 10.13224/j.cnki.jasp.2018.02.017

涵道比调节对核心机驱动风扇级与高压压气机匹配性能影响

doi: 10.13224/j.cnki.jasp.2018.02.017

Effects of bypass ratio on the matching performance between core driven fan stage and high pressure compressor

  • 摘要: 根据某核心机驱动风扇级与高压压气机匹配气动布局的特点,建立了匹配状态点关联预估简化方程并发展了匹配性能预估程序。基于两个压缩部件性能试验数据,进行了典型匹配状态涵道比预估及特点分析,研究了等转速下涵道比调节对两个压缩部件工作状态点变化规律以及匹配性能影响。结果表明:(1)涵道比设置不合理将会导致压缩部件发生旋转失速或喘振现象,从而影响两者的匹配工作;(2)随着涵道比增大,核心机驱动风扇级工况点逐渐从近喘点向堵塞点方向偏移,而高压压气机的工况点变化趋势正好相反。核心机驱动风扇级的流量变化范围比高压压气机的窄,这使得匹配总压比-流量特性线更加陡峭;(3)存在最佳匹配涵道比使稳定工作裕度和近失速边界匹配总压比达到最大,并且此时的匹配峰值总效率接近最大匹配峰值总效率;(4)随着匹配转速的提高,典型匹配涵道比呈现逐渐减小趋势,外涵流量在85%换算转速时达到最大,因此在进行外涵流道设计需全面考虑压气机的工作特性。

     

  • [1] 方昌德.变循环发动机[J].燃气涡轮试验与研究,2004,17(3):1-5.FANG Changde.Variable cycle engines[J].Gas Turbine Experiment and Research,2004,17(3):1-5.(in Chinese)
    [2] 方昌德.变循环发动机及其关键技术[J].国际航空,2004(7):49-51.FANG Changde.Variable cycle engine and its key technologies[J].International Aviation,2004(7):49-51.(in Chinese)
    [3] FISHBACH L H,STITT L E,STONE J,et al.NASA research in supersonic propulsion:a decade of progress[R].AIAA-82-1048,1982.
    [4] RALLABHANDI S K,MAVRIS D N.Simultaneous airframe and propulsion cycle optimization for supersonic aircraft design[J].Journal of Aircraft,2008,45(1):38-55.
    [5] FRENCH M W,ALLEN G L.NASA VCE test bed engine aerodynamic performance characteristics and results[R].AIAA-81-1594,1981.
    [6] VDOVIAK J W,KNOTT P R,EBACKER J A.Aerodynamic/ acoustic performance of YJ101/double bypass VCE with coannualr plug nozzle[R].NASA CR-159869,1981.
    [7] 张鑫,刘宝杰.紧凑布局核心机驱动风扇级设计参数影响分析[J].推进技术,2011,32(1):47-53.ZHANG Xin,LIU Baojie.Analysis of the core driven fan stage with compact aerodynamic configuration[J].Journal of Propulsion Technology,2011,32(1):47-53.(in Chinese)
    [8] 张鑫,刘宝杰.核心机驱动风扇级的气动设计特点分析[J].航空动力学报,2010,25(2):434-442.ZHANG Xin,LIU Baojie.Analysis of aerodynamic design of core driven fan stage[J].Journal of Aerospace Power,2010,25(2):434-442.(in Chinese)
    [9] 张鑫,刘宝杰.核心机驱动风扇级在非设计模式下的匹配方法研究[J].推进技术,2014,35(3):320-327.ZHANG Xi,LIU Baojie.Investigation of a methodology for the CDFS matching in the non-design operating mode[J].Journal of Propulsion Technology,2014,35(3):320-327.(in Chinese)
    [10] 张鑫,刘宝杰.核心机驱动风扇级匹配特性分析[J].航空学报,2015,36(9):2850-2858.ZHANG Xin,LIU Baojie.Matching characteristics of core driven fan stage[J].Acta Aeronautica et Astronautica Sinica,2015,36(9):2850-2858.(in Chinese)
    [11] 赖安卿.核心机驱动风扇级气动布局研究[D].南京:南京航空航天大学,2015.LAI Anqing.Research on aerodynamic design of core driven the aerodynamic design of the core driven fan stage[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2015.(in Chinese)
    [12] 赖安卿,胡骏,屠宝锋.核心机驱动风扇级气动设计方案[J].航空动力学报,2014,29(9):2229-2238.LAI Anqing,HU Jun,TU Baofeng.Scheme on aerodynamic design of core driven fan stage[J].Journal of Aerospace Power,2014,29(9):2229-2238.(in Chinese)
    [13] 赖安卿,陈淑仙,付为刚.核心机驱动风扇级转子叶尖流动结构和机理的研究[J].机械设计与制造,2015(12):38-41.LAI Anqing,CHEN Shuxian,FU Weigang.Research on rotor tip flow structure and mechanism of core driven fan stage[J].Machinery Design & Manufacture,2015(12):38-41.(in Chinese)
    [14] 赖安卿,付尧明,陈淑仙.弯曲叶片静子对核心机驱动风扇级的影响研究[J].机械设计与制造,2016(4):9-12.LAI Anqing,FU Yaoming,CHEN Shuxian.Core driven fan stage study on the effect of bowed stators vanes[J].Machinery Design & Manufacture,2016(4):9-12.(in Chinese)
    [15] 王前,胡骏,王爽.导向器稠度对核心机驱动风扇级性能的影响[J].机械设计与制造工程,2015,44(11):83-85.WANG Qian,HU Jun,WANG Shuang.The effect of inlet guide vanes solidity on core driven fan stage performance[J].Machine Design and Manufacturing Engineering,2015,44(11):83-85.(in Chinese)
    [16] 王前,胡骏,王爽.可变弯度导向器的基础叶型设计[J].机械设计与制造工程,2015,44(9):1-3.WANG Qian,HU Jun,WANG Shuang.Fundamental balde profile design for the variable camber vanes[J].Machine Design and Manufacturing Engineering,2015,44(9):1-3.(in Chinese)
    [17] 王前,胡骏,屠宝锋,等.核心机驱动风扇级可变弯度导叶设计方法[J].推进技术,2016,37(10):1855-1859.WANG Qian,HU Jun,TU Baofeng,et al.Method of variable camber inlet guide vanes design on core driven fan stage[J].Journal of Propulsion Technology,2016,37(10):1855-1859.(in Chinese)
    [18] 刘宝杰,贾少锋,于贤君.变循环核心压气机可调特性的数值研究[J].工程热物理学报,2016,37(9):1850-1855.LIU Baojie,JIA Shaofeng,YU Xianjun.Numerical study of the characteristic of a variable cycle core compressor[J].Journal of Engineering Thermodynamics,2016,37(9):1850-1855.(in Chinese)
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出版历程
  • 收稿日期:  2017-04-19
  • 刊出日期:  2018-02-28

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