Volume 30 Issue 7
Jul.  2015
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LIU Gao-wen, CHEN Kai, GANG Tie, ZHENG Hai-liang. Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well[J]. Journal of Aerospace Power, 2015, 30(7): 1554-1560. doi: 10.13224/j.cnki.jasp.2015.07.003
Citation: LIU Gao-wen, CHEN Kai, GANG Tie, ZHENG Hai-liang. Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well[J]. Journal of Aerospace Power, 2015, 30(7): 1554-1560. doi: 10.13224/j.cnki.jasp.2015.07.003

Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well

doi: 10.13224/j.cnki.jasp.2015.07.003
  • Received Date: 2014-01-22
  • Publish Date: 2015-07-28
  • To study the flow characteristics of a labyrinth seal in a compressor stator well, numerical simulations on the performances of a labyrinth seal with inlet and outlet rotating disc cavities of an aero-engine compressor was carried out. Sealing characteristics, swirl characteristics and windage heating characteristics were studied in depth at pressure ratio range 1.05-1.30 and Reynolds number range 100-50000. The differences of the flow characteristics of straight-through labyrinth with/without inlet and outlet rotating disc cavities were compared. The computational results show that inlet and outlet rotating disc cavities have obvious influence on the flow of the labyrinth. With the increase of pressure ratio, the discharge coefficient increases, and the sealing effect grows worse, while the outlet swirl ratio and windage heating decreases. With the increase of Reynolds number, the discharge coefficient increases significantly, the outlet swirl ratio and windage heating decreases. At high Reynolds number, the discharge coefficient, outlet swirl ratio and windage heating changes slightly.

     

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  • [1]
    Sturgess G J.Application of CFD to gas turbine engine secondary flow system:the labyrinth seal[R].AIAA 88-3203,1988.
    [2]
    徐再清,朱惠人,白江涛.航空发动机篦齿封严特性数值分析[J].机械设计与制造,2008,2(6):31-33. XU Zaiqing,ZHU Huiren,BAI Jiangtao.Numerical analysis of labyrinth seal in aircraft engines[J].Machinery Desigh and Manufacture,2008,2(6):31-33.(in Chinese)
    [3]
    纪国剑,吉洪湖.旋转状态下篦齿-蜂窝结构封严特性研究[J].工程热物理学报,2006,27(1):161-164. JI Guojian,JI Honghu.Investigation of sealing characteristics of labyrinth-honeycomb seal under rotating condition[J].Journal of Engineering Thermophysics,2006,27(1):161-164.(in Chinese)
    [4]
    Chougule H H,Ramerth D.Low leakage designs for rotor teeth and honeycomb lans in labyrinth seals[R].ASME Paper 2008-GT-51024,2008.
    [5]
    Weinberger T,Dullenkopf K,Bauer H J.Influence of honeycomb facings on the temperature distribution of labyrinth seals[R].ASME Paper 2010-GT-22069,2010.
    [6]
    Soemarwoto B I,Kok J C,de Cock K M J,et al.Performance evaluation of gas turbion labyrinth seals using computational fluid dynamics[R].ASME Paper 2007-GT-27905,2007.
    [7]
    纪国剑,吉洪湖,黄云霞,等.直通篦齿蜂窝封严结构的风阻特性试验[J].航空动力学报,2011,26(12):2655-2660. JI Guojian,JI Honghu,HUANG Yunxia,et al.Experiment investigation of windage heating on straight-through labyrinth seals with honeycomb bush[J].Journal of Aerospace Power,2011,26(12):2655-2660.(in Chinese)
    [8]
    杨汇涛,曹玉璋.旋转篦齿封严泄漏与换热的准则研究[J].北京航空航天大学学报,1999,25(4):438-441. YANG Huitao,CAO Yuzhang.Analogous criteria of leakage flow and heat transfer in labyrinth seals[J].Journal Beijing University of Aeronautics and Astronautics,1999,25(4):438-441.(in Chinese)
    [9]
    王锁芳,吕海峰.转静态封严篦齿流场的数值分析和封严特性的研究[J].航空动力学报,2005,20(3):444-449. WANG Suofang,LV Haifeng.Numerical analysis of flow and experimental investigation of labyrinth sealing characteristics at rotational and static states[J].Journal of Aerospace Power,2005,20(3):444-449.(in Chinese)
    [10]
    王代军,苏云亮,罗翔.旋转状态下篦齿流量特性试验研究[J].燃气涡轮试验与研究,2007,20(2):41-44. WANG Daijun,SU Yuliang,LUO Xiang.Experimental investigation on leakage flow characteristics in rotating labyrinth seals[J].Gas Turbine Experiment and Research,2007,20(2):41-44.(in Chinese)
    [11]
    王鹏飞,郭文,刘玉芳,等.直通式篦齿封严特性的数值分析和试验研究[J].燃气涡轮试验与研究,2009,22(1):32-36. WANG Pengfei,GUO Wen,LIU Yufang,et al.Numerical analysis and experimental investigation of straight-through labyrinth sealing characteristic[J].Gas Turbine Experiment and Research,2009,22(1):32-36.(in Chinese)
    [12]
    王鹏飞,刘玉芳,郭文,等.高转速对直通型篦齿封严特性影响的试验研究[J].燃气涡轮试验与研究,2007,20(2):45-48. WANG Pengfei,LIU Yufang,GUO Wen,et al.Influence of high rotational speeds on the labyrinth sealing characteristics[J].Gas Turbine Experiment and Research,2007,20(2):45-48.(in Chinese)
    [13]
    LI Jun,YAN Xin,FENG Zhenping.Effects of pressure ratio and fin pitch on leakage flow characteristics in high rotating labyrinth seals[R].AEME Paper 2006-GT-91145,2006.
    [14]
    张霞,张效伟,朱惠人,等.直通型篦齿封严特性的研究[J].航空动力学报,2010,25(8):1753-1756. ZHANG Xia,ZHANG Xiaowei,ZHU Huiren,et al.Experimental investigation on seal characteristics of straight-through labyrinth[J].Journal of Aerospace Power,2010,25(8):1753-1756.(in Chinese)
    [15]
    Gamal A M,Vance J M.Labyrinth seal leakage tests:tooth profile,tooth thickness,and eccentricity effects[R].ASME Paper 2007-GT-27223,2007.
    [16]
    Denecke J,Dullenkopf K,Wittig S,et al.Experimental investigation of the total temperature increase and swirl development in rotating labyrinth seals[R].ASME Paper 2005-GT-68677,2005.
    [17]
    吴宏,李澎,陶智.直齿直通式篦齿封严计算模型[J].航空动力学报,2012,27(10):2180-2187. WU Hong,LI Peng,TAO Zhi.Rectangular tooth straight through labyrinth seal analytical modal[J].Journal of Aerospace Power,2012,27(10):2180-2187.(in Chinese)
    [18]
    Willenborg K,Kim S,Wittig S.Effects of Reynolds number and pressure ratio on leakage loss and heat transfer in a stepped labyrinth seal[R].ASME Paper 2001-GT-0123,2001.
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