留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

多级轴流压气机S2正问题气动性能优化

郭义,  杜刚,  陈江,  尹红顺

downloadPDF
文章导航 > 航空动力学报  > 2012 >  27(4): 953-960
郭义, 杜刚, 陈江, 尹红顺. 多级轴流压气机S2正问题气动性能优化[J]. 航空动力学报, 2012, 27(4): 953-960.
引用本文: 郭义, 杜刚, 陈江, 尹红顺. 多级轴流压气机S2正问题气动性能优化[J]. 航空动力学报, 2012, 27(4): 953-960.
shu
GUO Yi, DU Gang, CHEN Jiang, YIN Hong-shun. Aerodynamic performance optimization on S2 analysis code of multi-stage axial compressor[J]. Journal of Aerospace Power, 2012, 27(4): 953-960.
Citation: GUO Yi, DU Gang, CHEN Jiang, YIN Hong-shun. Aerodynamic performance optimization on S2 analysis code of multi-stage axial compressor[J]. Journal of Aerospace Power, 2012, 27(4): 953-960.
shu

多级轴流压气机S2正问题气动性能优化

  • 1.

    北京航空航天大学 能源与动力工程学院, 北京 100191

  • 2.

    中国航空工业集团公司 中国燃气涡轮研究院, 成都 610500

Aerodynamic performance optimization on S2 analysis code of multi-stage axial compressor

  • 1.

    School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2.

    China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China

    摘要
  • 摘要: 将求解多级轴流压气机特性的S2正问题计算程序集成在ISIGHT优化软件上,构建压气机S2正问题气动性能优化平台.针对某4级轴流压气机,通过调整沿径向截面的叶栅弯角、叶栅稠度、叶型最大相对厚度等参数,考核设计几何参数对S2正问题计算效率目标函数的影响程度,择优选取设计参数作为优化变量,建立响应面模型,结合遗传算法,对目标函数进行优化.结果显示压气机特性整体提高,设计点压比增加19.6%,效率提高4.66%,折合转速1.0下的稳定裕度增大到22.32%,验证了构建优化平台在压气机气动设计中的实用价值,可供内流叶轮机气动性能优化设计参考.

     

    Abstract: An aerodynamic performance optimization platform was established for S2 analysis code of compressor by integrating the ISIGHT optimization software and S2 analysis code which calculated performance of multi-stage axial compressor.When a four-stages axial-flow compressor was optimized,the parameters were selected by adjusting blade camber angle,solidity,relative maximum thickness and so on,along radial which have more influence on the objective function just like efficiency to establish the response surface model and integrated evolutionary algorithm to optimize the objective function.The result shows that the whole characteristic of compressor improves,pressure ratio increases 19.6% and efficiency increases 4.66% at design point,stall margin increases to 22.32% at 1.0 equivalent rotor-speed,which proves that building optimization platform has practical value for aerodynamic design of compressor,and can be reference for aerodynamic performance optimization of inner flow tubromachinery.

     

    • HTML
    • 参考文献(13)
  • [1] 戴韧,王洪光,杨爱玲,等.叶轮S2流面气动半反问题通用解法的改进[J].工 程热物理学报,2009,30(10):1655-1658. DAI Ren,WANG Hongguang,YANG Ailing,et al.Improved and unified S2 through flow model for inverse problem in turbomachinery[J].Journal of Engineering Thermophysics,2009,30(10):1655-1658.(in Chinese)
    [2] Wright L C,Novak R A.Aerodynamic design and development of the general electric CJ805-23 aft fan component.ASME Paper 60-WA-270,1960.
    [3] 厉海涛,宋立明,李颖晨,等.基于控制理论和N-S方程的二维叶栅气动优化算法[J].工程热物理学报,2009,30(12):2021-2024. LI Haitao,SONG Liming,LI Yingchen.2D aerodynamic optimization algorithm for turbine blades based on control theory and N-S equation[J].Journal of Engineering Thermophysics,2009,30(12):2021-2024.(in Chinese)
    [4] 程荣辉,雷丕霓,刘波,等.一种工程实用的多级轴流压气机特性二维数值计算方法[J].航空动力学报,2007,22(6):955-960. CHENG Ronghui,LEI Pini,LIU Bo,et al.A two dimension numerical method for multi-stage axial compressor performance in engineering applications[J].Journal of Aerospace Power,2007,22(6):955-960.(in Chinese)
    [5] 塔雷金娜,别辽耶夫,左尼金.基于轴对称模型(正问题),多极轴流压气机的数值优化[M].沈阳:沈阳航空发动机设计研究所,1993.
    [6] 陈江,季路成.多级轴流压气机气动特性优化[J].工程热物理学报,2007,28(4):583-585. CHEN Jiang,JI Lucheng.Aerodynamic characteristic optimization of a multistage axial flow compressor[J].Journal of Engineering Thermophysics,2007,28(4):583-585.(in Chinese)
    [7] Lepsch R A,Mcmillin M L,Unal R.Response surface model building and multidisciplinary optimization using D-optimal designs.AIAA-98-4759,2006.
    [8] 王晓峰,席光,王尚锦.离心压缩机叶轮的响应面优化设计Ⅰ:设计方法[J].工程热物理学报,2004,25(3):408-410. WANG Xiaofeng,XI Guang,WANG Shangjin.Response surface methodology for centrifugal compressor impeller optimization design PartⅠ:design method[J].Journal of Engineering Thermophysics,2004,25(3):408-410.(in Chinese)
    [9] 席光,王志恒,王尚锦.叶轮机械气动优化设计中的近似模型方法及其应用[J].西安交通大学学报,2007,41(2):125-135. XI Guang,WANG Zhiheng,WANG Shangjin.Aerodynamic optimization design of turbomachinery with approximation model method[J].Journal of Xi’an Jiao Tong University,2007,41(2):125-135.(in Chinese)
    [10] 张晓东,吴虎,黄健,等.跨声速轴流压气机叶片周向弯曲的数值优化[J].航空动力学报,2008,23(10):1908-1912. ZHANG Xiaodong,WU Hu,HUANG Jian,et al.Numerical optimization of transonic axial compressor by bowed blades[J].Journal of Aerospace Power,2008,23(10):1908-1912.(in Chinese)
    [11] Lian Y S and Liou M S.Multiobjective optimization using coupled response surface model and evolutionary algorithm.AIAA-2004-4323,2004.
    [12] 宋立明,罗常,李军,等.基于全局气动优化方法的跨声速叶栅气动优化[J].航空动力 学报,2008,23(6):1019-1023. SONG Liming,LUO Chang,LI Jun,et al.Aerodynamic optimization of transonic cascade using global aerodynamic optimization method[J].Journal of Aerospace Power,2008,23(6):1019-1023.(in Chinese)
    [13] Oyama A,Liou M S.Multiobjective optimization of a multi-stage compressor using evolutionary algorithm.AIAA-2002-3535,2002.
    • 相关文章
    • 施引文献
  • 资源附件(0)
  • 加载中
WeChat 点击查看大图
计量
  • 文章访问数:  2112
  • HTML浏览量:  369
  • PDF量:  549
  • 被引次数: 0
出版历程
  • 收稿日期:  2011-05-03
  • 修回日期:  2011-10-10
  • 刊出日期:  2012-04-28

目录

    /

    返回文章
    返回

    版权所有 © 《航空动力学报》编辑部

    本系统由 北京仁和汇智信息技术有限公司 开发