Volume 31 Issue 8
Aug.  2016
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2016  >  31(8): 1943-1949
TU Bao-feng, LIU Hua, HU Jun. Study on improvement of the compressor anti-swirl distortion capacity with bowed stator[J]. Journal of Aerospace Power, 2016, 31(8): 1943-1949. doi: 10.13224/j.cnki.jasp.2016.08.020
Citation: TU Bao-feng, LIU Hua, HU Jun. Study on improvement of the compressor anti-swirl distortion capacity with bowed stator[J]. Journal of Aerospace Power, 2016, 31(8): 1943-1949. doi: 10.13224/j.cnki.jasp.2016.08.020
shu

Study on improvement of the compressor anti-swirl distortion capacity with bowed stator

doi: 10.13224/j.cnki.jasp.2016.08.020

  • 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

  • Received Date: 2014-11-13
  • Publish Date: 2016-08-28
    Abstract
  • In order to reduce the effect of swirl distortion on performance and stability of axial compressor, the first-stage stator of two-stage low speed axial compressor was designed into bowed blade with three different positive bending angles. A full annulus three-dimensional steady simulation method was used to investigate the effect of twin swirl on performance and stability of compressor. The results show that stator with appropriate positive bending design can improve the anti-twin swirl capacity of compressor. By reducing the load of blade at end wall regions using bowed stator blades, the suction surface boundary layer separation at hub will be decreased, loss will be reduced, and both of efficiency and total pressure ratio will be increased as a result. The maximum efficiency can be increased by 1.5% and mass flow rate at stall boundary point can be decreased by 6.95% when bending angles of stator blades equal to 10 degree. The efficiency and total pressure ratio will be increased by 1.7% and 0.03% respectively when mass flow rate equals to 18.5kg/s. Load at mid-span region and friction loss will increase when bending angle is too large, making it harmful to improve the efficiency and total pressure ratio.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    Genssler H P,Meyer W,Fottner L.Development of intake swirl generators for turbo jet engine testing[C]//Proceedings of Engine Response to Distorted Inflow Conditions.Munich:Advisory Group for Aerospace Research and Development,1987:18.1-18.21.
    [2]
    Aranake A,Jin G L,Knight D,et al.Automated design optimization of a three-dimensional subsonic diffuser[J].Journal of Propulsion and Power,2011,27(4):838-846.
    [3]
    Magnus T.Design andanalysis of compact UAV ducts[R].AIAA-2006-2828,2006.
    [4]
    甘文彪,周洲,许晓平,等.S弯进气道优化设计及分析[J].推进技术,2014,35(10):1317-1324. GAN Wenbiao,ZHOU Zhou,XU Xiaoping,et al.S-duct inlet optimal design and analysis[J].Journal of Propulsion Technology,2014,35(10):1317-1324.(in Chinese)
    [5]
    谢文忠,郭荣伟.蛇形进气道涡控设计研究[J].航空学报,2011,32(10):1806-1814. XIE Wenzhong,GUO Rongwei.Vortex controlled design research for serpentine inlet[J].Acta Aeronautica et Astronautica Sinica,2011,32(10):1806-1814.(in Chinese)
    [6]
    张振,刘丹,黄浩.S弯进气道流动控制技术的试验研究[J].应用力学学报,2014,31(2):201-205. ZHANG Zhen,LIU Dan,HUANG Hao.Experimental investigation on flow control in S-shaped inlet[J].Chinese Journal of Applied Mechanics,2014,31(2):201-205.(in Chinese)
    [7]
    Harper D K,Burdisso R A,Leitch T A,et al.Boundary layer control and wall-pressure fluctuations in a serpentine inlets[R].AIAA-2000-3597,2000.
    [8]
    Owen L R,Allan B G,Gorton S A.Boundary-layer-ingesting inlet flow control[R].AIAA-2006-839,2006.
    [9]
    Sullerey R K,Mangat V S,Padhi A.Flow control in serpentine inlet using vortex generator jets[R].AIAA-2006-3499,2006.
    [10]
    Harrison N A,Anderson J,Fleming J L.Experimental investigation of active flow control of a boundary layer ingesting serpentine inlet diffuser[R].AIAA-2007-843,2007.
    [11]
    Harouni A G.Flow control of a boundary layer ingesting serpentine diffuser via blowing and suction[J].Aerospace Science and Technology,2014,39(12):472-480.
    [12]
    李斌斌,陈克明,顾蕴松.斜出口合成射流激励器S进气道分离流动控制[J].实验流体力学,2012,26(2):34-37. LI Binbin,CHEN Keming,GU Yunsong.Separation flow control of beveled synthetic jet actuator in S-shaped inlet[J].Journal of Experiments in Fluid Mechanics,2012,26(2):34-37.(in Chinese)
    [13]
    郭荣伟,梁德旺,陈贻忠.进口导流叶片对S弯进气道出口旋流的抑制研究[J].空气动力学学报,1996,14(2):141-147. GUO Rongwei,LIANG Dewang,CHEN Yizhong.Investigation on swirl control in a diffusing S-shaped inlet with a horizontal guiding fence[J].Acta Aerodynamica Sinica,1996,14(2):141-147.(in Chinese)
    [14]
    Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall[R].ASME Paper GT2005-66048,2005.
    [15]
    Breugelmans F A E.Influence of incidence angle on the secondary flow in compressor cascade with different dihedral distribution[R].ISABE Paper 85-7078,1985.
    [16]
    Shang E,Wang Z Q,Su J X.The experimental investigations on the compressor cascades with leaned and curved blades[R].ASME Paper 93-GT-50,1993.
    [17]
    Weingold H D,Neubert R J,Behlke R F.Bowed stator:an example of CFD applied to improve multistage compressor efficiency[J].Journal of Turbomachinery,1997,119(1):161-168.
    [18]
    Fischer A.Performance of strongly bowed stators in a 4-stage high speed compressor[R].ASME Paper GT2003-38392,2003.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 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
    Get Citation
    PDF(1358.0KB)
    XML

    Article Metrics

    Article views (1043) PDF downloads(647) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return