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跨声速轴流压气机失速边界预测方法

钟勇健 滕金芳 徐玺 羌晓青 吴亚东 欧阳华

钟勇健, 滕金芳, 徐玺, 羌晓青, 吴亚东, 欧阳华. 跨声速轴流压气机失速边界预测方法[J]. 航空动力学报, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012
引用本文: 钟勇健, 滕金芳, 徐玺, 羌晓青, 吴亚东, 欧阳华. 跨声速轴流压气机失速边界预测方法[J]. 航空动力学报, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012
ZHONG Yong-jian, TENG Jin-fang, XU Xi, QIANG Xiao-qing, WU Ya-dong, OUYANG Hua. Prediction method of stall margin in axial-flow transonic compressor[J]. Journal of Aerospace Power, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012
Citation: ZHONG Yong-jian, TENG Jin-fang, XU Xi, QIANG Xiao-qing, WU Ya-dong, OUYANG Hua. Prediction method of stall margin in axial-flow transonic compressor[J]. Journal of Aerospace Power, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012

跨声速轴流压气机失速边界预测方法

doi: 10.13224/j.cnki.jasp.2014.08.012
基金项目: 

国家自然科学基金(11202132)

详细信息
    作者简介:

    钟勇健(1988-),男,上海人,硕士,研究方向为轴流压气机气动设计。

  • 中图分类号: V231.3

Prediction method of stall margin in axial-flow transonic compressor

  • 摘要: 研究了跨声速、单级设计压比为1.82的Stage 35轴流压气机与单级设计压比为2.05的Stage 37轴流压气机在不同转速下的特性.在HARIKA原型程序基础上,改进了其叶排效率、落后角、理论能头计算模型,采用了两种轴流压气机失速边界的预测方法,第1种为HARIKA原型程序的分离流量预测方法,第2种为Koch所提出的失速静压升系数预测方法,所得特性计算结果与实验点吻合较好,Stage 35设计点效率的误差由原型的3.9%降低到改进后的1.5%,Stage 37设计点效率的误差由3.1%降低到1.9%.两种预测方法对失速边界流量的预测误差最小分别可达1.3%与1.6%,表明两种失速边界预测方法都是可行的.

     

  • [1] Koch C C.Stalling pressure rise capability of axial flow compressor stages[J].Journal of Engineering for Power,1981,103(4):645-656.
    [2] Smith L H,Jr.Axial compressor aerodesign evolution at general electric[J].Journal of Turbomachinery,2002,124(3):321-330.
    [3] Farokhi S.Aircraft propulsion[M].Lawrence,US:University of Kansas Press,2007.
    [4] Cumpsty N A.Compressor aerodynamics[M].London:University of Cambridge Press,1989.
    [5] Falck N.Axial flow compressor mean line design[D].Lund,Sweden:Lund University,2008.
    [6] 胡俊.均匀与非均匀进气条件下多级轴流压气机性能计算:均匀进气及径向畸变的影响[J].航空动力学报,2000,15(3):225-228. HU Jun.Calculation of off-design performance of multistage compressors with uniform and radial distorted inlet flow[J].Journal of Aerospace Power,2000,15(3):225-228.(in Chinese)
    [7] 吴艳辉,朱俊强,刘志伟.多级轴流压气机机匣处理级的探讨[J].航空动力学报,2002,17(5):542-548. WU Yanhui,ZHU Junqiang,LIU Zhiwei.Research on the axial position of treated casing in multistage axial-flow compressors[J].Journal of Aerospace Power,2002,17(5):542-548.(in Chinese)
    [8] 王英锋,胡骏.雷诺数对轴流压气机稳定性的影响[J].航空动力学报,2004,19(1):69-73. WANG Yingfeng,HU Jun.The effects of Reynolds number on the stability of axial compressors[J].Journal of Aerospace Power,2004,19(1):69-73.(in Chinese)
    [9] 王英锋,胡骏.雷诺数对轴流风扇/压气机性能和稳定性的影响[J].南京航空航天大学学报,2004,36(2):145-149. WANG Yingfeng,HU Jun.Effects of Reynolds number on performance and stability of axial fans/compressors[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(2):145-149.(in Chinese)
    [10] 楚武利,王毅,杨泳.多级轴流压气机率先失速级的预测方法研究[J].流体机械,2005,33(10):11-14. CHU Wuli,WANG Yi,YANG Yong.Prediction method investigation of rotating stall stage in multi-stage axial flow compressor[J].Fluid Machinery,2005,33(10):11-14.(in Chinese)
    [11] 赵勇,胡骏,屠宝锋,等.多级轴流风扇/压气机非设计点性能计算方法[J].推进技术,2008,29(2):219-224. ZHAO Yong,HU Jun,TU Baofeng,et al.Calculation of multistage axial fan/compressor off-design performance[J].Journal of Propulsion Technology,2008,29(2):219-224.(in Chinese)
    [12] Veres J P.Axial and centrifugal compressor mean line flow analysis method[R].AIAA-2009-1641,2009.
    [13] Koch C C,Smith L H.Loss sources and magnitudes in axial-flow compressors[J].Journal of Engineering for Power,1976,98(3):411-424.
    [14] Boyer K M,O'Brien W F.An improved streamline curvature approach for off-design analysis of transonic axial compression systems[J].Journal of Turbomachinery,2003,125(3):475-481.
    [15] Reid L,Moore R D.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 1.82[R].NASA TP-1338,1978.
    [16] Moore R D,Reid L.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 2.05 .NASA TP-1659,1980.
    [17] Davis R L,Yao J.Prediction of compressor stage performance from choke through stall[R].AIAA-2005-1005,2005.
    [18] Davis R L,Yao K.Computational approach for predicting stall inception in multistage axial compressors[J].Journal of Propulsion and Power,2007,23(2):257-265.
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出版历程
  • 收稿日期:  2013-05-14
  • 刊出日期:  2014-08-28

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