基于逆向射流抑制封严篦齿泄漏流动的数值及实验研究
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摘要
针对一直通型篦齿通道进行了二维数值模拟,建立了9种封严结构模型,重点研究了位置和角度变化时逆向射流对篦齿内部流场的影响,探讨了不同模型下篦齿前后压比与泄漏系数的关系,发现各工况下的逆向射流在一定程度上都能够增强篦齿的封严效果,并且射流角度越小,密封性能越佳,射流位置在第一节齿腔中间时,抑制泄漏的效果最佳,当射流角为45°,射流位置在第一齿腔中间时,泄漏系数相对不带逆向射流时能够降低11.5%。在此基础上,进行了带逆向射流的二维直通型封严篦齿实验,在不同的压比下,用PIV分别测量了3种射流角度和3种射流位置下的篦齿通道内部流场,实验结果与数值计算变化规律一致。
Two-dimensional numerical simulations were performed for a straight labyrinth seal passage,nine kinds of sealing structure model were established,the effects of reverse jets at different positions and angles on the internal flow field of the labyrinth were studied emphatically,and the relationship between the front and back pressure ratio of the labyrinth and the leakage coefficient under different models was discussed.The results show that all different jet positions and angles can enhance the seal effect of labyrinth seal,the smaller jet angle,means the better sealing effect,when the jet position was in the middle of the first section of the tooth cavity,the leakage effect was the best.When the jet angleθwas45°and the jet position was in the middle of the first tooth cavity,the leakage coefficient can be reduced by 11.5%corresponding to the case without reverse jets.On the basis of numerical simulation,a two-dimensional straight labyrinth seal experiment with reverse jet was proceeded,using PIV to obtain the flow field with reverser jet under three jet angles and three jet positions,the experimental results were consistent with the calculated variation law.
Two-dimensional numerical simulations were performed for a straight labyrinth seal passage,nine kinds of sealing structure model were established,the effects of reverse jets at different positions and angles on the internal flow field of the labyrinth were studied emphatically,and the relationship between the front and back pressure ratio of the labyrinth and the leakage coefficient under different models was discussed.The results show that all different jet positions and angles can enhance the seal effect of labyrinth seal,the smaller jet angle,means the better sealing effect,when the jet position was in the middle of the first section of the tooth cavity,the leakage effect was the best.When the jet angleθwas45°and the jet position was in the middle of the first tooth cavity,the leakage coefficient can be reduced by 11.5%corresponding to the case without reverse jets.On the basis of numerical simulation,a two-dimensional straight labyrinth seal experiment with reverse jet was proceeded,using PIV to obtain the flow field with reverser jet under three jet angles and three jet positions,the experimental results were consistent with the calculated variation law.
引文
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[16]傅鑫,曹永华,张一彬,等.基于一种泄漏流边界模型的封严篦齿分析方法研究[J].兵工学报2017,38(4):824-832.FU Xin,CAO Yonghua,ZHANG Yibin,et al.Study of leakage flow boundary model-based sealing labyrinth analysis method[J].Acta Armamentarii,2017,38(4):824-832.(in Chinese)
[17] STOCKER H L.Determining and improving labyrinth seal performance in current and advanced high performance gas turbines[R].AGARD CP-237,1978.
[18] MARGARET P P.High-speed high-temperature finger seal test results[R].NASA/TM2002-211589,2002.
[19]纪国剑.航空发动机典型篦齿封严泄漏特性的数值和实验研究[D].南京航空航天大学,2008.JI Guojian.Numerical and experimental investigation of sealing characteristics on typical labyrinth seals in aeroengine[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[20]孟德君,邢雷,李坚.篦齿封严流动及其对压气机静子性能的影响[J].航空发动机,2013,39(6):31-35,42.MENG Dejun,XING Lei,LI Jian.Influence of shrouded stator cavity flow on compressor stator performance[J].Aeroengine,2013,39(6):31-35,42.(in Chinese)
[2] WELLBORN S R,OKIISHI T H.The influence of shrouded stator cavity flows on multistage compressor performance[J].Journal of Turbomachinery,1999,121(3):486-497.
[3] WELLBORN S R,TOLCHINSKY I.Modeling shrouded stator cavity flows in axial flow compressors[J].Journal of Turbomachinery,2000,122(1):55-61.
[4] BUNKER R S.Axial turbine blade tips:function,design,and durability[J].Journal of Propulsion&Power,2012,22(2):271-285.
[5]沈虹,郑天慧,陈玉洁.航空发动机封严技术的进展[J].燃气涡轮实验与研究,2011,24(4):51-55.SHEN Hong,ZHENG Tianhui,CHEN Yujie.Improvement of aero-engine sealing technology[J].Gas Turbine Experiment and Research,2011,24(4):51-55.(in Chinese)
[6]王锁芳,吕海峰,夏登勇.封严篦齿结构特性的数值分析和实验研究[J].南京航空航天大学学报,2004,36(6):732-735.WANG Suofang,LHaifeng,XIA Dengyong.Numerical analyses and experimental investigations of seal labyrinth characteristics[J].Journal of Nanjing University of Aeronautics&Astronautics,2004,36(6):732-735.(in Chinese)
[7]纪国剑,吉洪湖.直通篦齿封严结构压损规律和临界特性的研究[J].航空动力学报,2008,23(3):417-420.JI Guojian,JI Honghu.Numerical and experimental investigation of pressure loss and critical sealing characteristics of straight-through labyrinth seals[J].Journal of Aerospace Power,2008,23(3):417-420.(in Chinese)
[8]杜发青,吉洪湖,帅海山,等.齿形几何参数对直通篦齿封严泄漏特性影响的正交实验[J].航空动力学报,2013,28(4):825-831.DU Faqing,JI Honghu,SHUAI Haishan,et al.Orthogonal experiment of effect of fin geometrical parameters on leakage of straight-through labyrinth seals[J].Journal of Aerospace Power,2013,28(4):825-831.(in Chinese)
[9]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(6):31-33.XU Zaiqing,ZHU Huiren,BAI Jiangtao.Numerical analysis of labyrinth seal in aircraft engines[J].Machinery Design&Manufacture,2008(6):31-33.(in Chinese)
[10]张勃,吉洪湖,杜发青,等.基于正交法的直通篦齿封严齿形几何参数对换热特性影响的实验研究[J].机械工程学报,2013,49(4):134-139.ZHANG Bo,JI Honghu,DU Faqing,et al.Orthogonal design experimental investigation of effect of tip geometrical parameters on heat transfer of straight-through labyrinth[J].Journal of Mechanical Engineering,2013,49(4):134-139.(in Chinese)
[11]王建中,黄守龙.直通式迷宫密封的静态工作特性[J].武汉工业大学学报,1994,16(4):86-90.WANG Jianzhong,HUANG Shoulong.Experimental study on static features for straight-through labyrinth seal[J].Journal of Wuhan University of Technology,1994,16(4):86-90.(in Chinese)
[12]张效伟,朱惠人,张霞,等.直通型篦齿泄漏的特性试验[J].航空动力学报,2011,26(9):1970-1974.ZHANG Xiaowei,ZHU Huiren,ZHANG Xia,et al.Experiment on discharge characteristics of straight-through labyrinth[J].Journal of Aerospace Power,2011,26(9):1970-1974.(in Chinese)
[13]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实验研究[J].燃气涡轮实验与研究,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)
[14]塔鲁达纳夫斯基.非接触密封:间隙密封与迷宫密封的原理和应用[M].北京:机械工业出版社,1986.
[15]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试验[J].航空动力学报,2005,20(3):444-449.WANG Suofang,LHaifeng.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)
[16]傅鑫,曹永华,张一彬,等.基于一种泄漏流边界模型的封严篦齿分析方法研究[J].兵工学报2017,38(4):824-832.FU Xin,CAO Yonghua,ZHANG Yibin,et al.Study of leakage flow boundary model-based sealing labyrinth analysis method[J].Acta Armamentarii,2017,38(4):824-832.(in Chinese)
[17] STOCKER H L.Determining and improving labyrinth seal performance in current and advanced high performance gas turbines[R].AGARD CP-237,1978.
[18] MARGARET P P.High-speed high-temperature finger seal test results[R].NASA/TM2002-211589,2002.
[19]纪国剑.航空发动机典型篦齿封严泄漏特性的数值和实验研究[D].南京航空航天大学,2008.JI Guojian.Numerical and experimental investigation of sealing characteristics on typical labyrinth seals in aeroengine[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[20]孟德君,邢雷,李坚.篦齿封严流动及其对压气机静子性能的影响[J].航空发动机,2013,39(6):31-35,42.MENG Dejun,XING Lei,LI Jian.Influence of shrouded stator cavity flow on compressor stator performance[J].Aeroengine,2013,39(6):31-35,42.(in Chinese)