基于一种泄漏流边界模型的封严篦齿分析方法研究
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摘要
针对篦齿通道中存在的结构相对复杂、封严间隙随工作状态变化、数值模拟计算域网格量大等问题,对不同密封构型参数下的多种直通式封严篦齿模型进行了高速实验研究,并基于实验结果建立能够反映环境参数和封严构型参数对密封性能影响的篦齿泄漏流边界模型。结果表明:该模型能够很好地还原实验规律,可以在多级的压气机计算中可靠地模拟篦齿泄漏流动,并在某3级压气机中计算得到0.5%的泄漏量将分别导致压气机流量、压比和效率呈现1.4%、0.3%和1.1%的下降。
In view of the complex structure of labyrinth channel,changing sealing gap and a large amount of grids in numerical simulation calculation domain,a high-speed straight-through sealing labyrinth structure adopting different sealing configuration parameters is investigated. A labyrinth leakage flow boundary model is established based on test results,which can reveal the effects of environmental parameters and sealing configuration parameters on sealing property. The results show that the proposed model can be used to repeat the experimental rule and reliably simulate the labyrinth leakage flow in multistage compressor. The calculated sresult shows that 0. 5% flow leakage would result in decreasing the flow,pressure ratio and efficiency of a three-stage compressor by 1. 4%,0. 3% and 1. 1%,respectively.
In view of the complex structure of labyrinth channel,changing sealing gap and a large amount of grids in numerical simulation calculation domain,a high-speed straight-through sealing labyrinth structure adopting different sealing configuration parameters is investigated. A labyrinth leakage flow boundary model is established based on test results,which can reveal the effects of environmental parameters and sealing configuration parameters on sealing property. The results show that the proposed model can be used to repeat the experimental rule and reliably simulate the labyrinth leakage flow in multistage compressor. The calculated sresult shows that 0. 5% flow leakage would result in decreasing the flow,pressure ratio and efficiency of a three-stage compressor by 1. 4%,0. 3% and 1. 1%,respectively.
引文
[1]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:南京航空航天大学,2008.JI Guo-jian.Numerical and experimental investigation of sealing characteristics on typical labyrinth seals in aeroengine[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[2]沈虹,郑天慧,陈玉洁.航空发动机封严技术的进展[J].燃气涡轮试验与研究,2011,24(4):51-55.SHEN Hong,ZHENG Tian-hui,CHEN Yu-jie.Improvement of aero-engine sealing technology[J].Gas Turbine Experiment and Research,2011,24(4):51-55.(in Chinese)
[3]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.
[4]禄堃.轴流压气机静叶气封间隙流的研究和流道优化[D].北京:清华大学,2008.LU Kun.Research on axial-compressor shrouded stator cavity flows and flow path optimization[D].Beijing:Tsinghua University,2008.(in Chinese)
[5]Gier J,Stubert B,Brouillet B,et al.Interaction of shroud leakage flow and main flow in a three-stage LP turbine[J].Journal of Turbomachinery,2003,127(4):105-116.
[6]马文生,禄堃,顾春伟.压气机静叶气封几何优化与流动分析[J].工程热物理学报,2009,30(8):1288-1290.MA Wen-sheng,LU Kun,GU Chun-wei.Compressor stator seal cavity geometry optimization and flow analysis[J].Journal of Engineering Thermophysics,2009,30(8):1288-1290.(in Chinese)
[7]应银生,马石.叶冠齿数和齿顶间隙对涡轮气动性能的影响[J].航空制造技术,2016,496(1/2):128-131.YING Yin-sheng,MA Shi.Effect of the shroud seal number and the tip clearance on the aerodynamic performance of the turbine[J].Aeronautical Manufacturing Technology,2016,496(1/2):128-131.(in Chinese)
[8]温泉,梁德旺,王可.旋转直管流场的数值模拟[J].南京航空航天大学学报,2000,32(5):539-544.WEN Quan,LIANG De-wang,WANG Ke.Rotary straight pipe field numerical simulation[J].Journal of Nanjing University of Aeronautics&Astronautics,2000,32(5):539-544.
[9]Kuwamura Y,Matsumoto K,Uehara H,et al.Development of new high-performance labyrinth seal using aerodynamic approach[C]∥ASME Turbo Expo 2013:Turbine Technical Conference and Exposition.San Antonio,Texas,US:ASME,2013.
[10]Rhode D L,Allen B F.Measurement and visualization of leakage effects of rounded teeth tips and rub-grooves on stepped labyrinths[J].Journal of Engineering for Gas Turbines&Power,1999,123(3):604-611.
[11]张勃,吉洪湖,杜发青,等.篦齿封严尺寸缩放与气流温度变化对流动与传热影响实验研究[J].推进技术,2016,37(2):304-310.ZHANG Bo,JI Hong-hu,DU Fa-qing,et al.Experimental investigation of scaling and temperature effects on flowing and heat transfer characteristics in labyrinth seals[J].Journal of Propulsion Technology,2016,37(2):304-310.(in Chinese)
[12]塔鲁达纳斯基.非接触密封/间隙密封与迷宫密封的原理和应用[M].李均卿,刁元康,译.北京:机械工业出版社,1986.Trutnovsky K.Berührungsfreie dichtungen:grundlagen und anwendungen der str9mung durch spalte und labyrinth[M].LI Junqing,DIAO Yuan-kang,translated.Beijing:China Machine Press,1986.(in Chinese)
[13]Stocker H L.Determining and improving labyrinth seal performance in current and advanced high performance gas turbines[J].AGARD Conference Proceedings,1978,237:13.
[14]赵海刚,刘振侠.航空发动机篦齿封严特性数值模拟[J].燃气涡轮实验与研究,2010,23(1):26-30.ZHAO Hai-gang,LIU Zhen-xia.Numerical analyses for the performance of straight labyrinth seal of aircraft engine[J].Gas Turbine Experiment and Research,2010,23(1):26-30.(in Chinese)
[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实验[J].航空动力学报,2005,20(3):444-449.WANG Suo-fang,LYU Hai-feng.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]吴丁毅.两类常用篦齿密封和临界特性的分析与比较[J].航空动力学报,1997,12(4):397-400.WU Ding-yi.Two types of commonly used grate tooth seal and critical features analysis and comparison[J].Journal of Aerospace Power,1997,12(4):397-400.(in Chinese)
[17]朱高涛,刘卫华.迷宫密封泄漏量计算方法的分析[J].润滑与密封,2006(4):123-126.ZHU Gao-tao,LIU Wei-hua.Analysis of calculational methods on leakage for labyrinth seals[J].Lubrication Engineering,2006(4):123-126.(in Chinese)
[2]沈虹,郑天慧,陈玉洁.航空发动机封严技术的进展[J].燃气涡轮试验与研究,2011,24(4):51-55.SHEN Hong,ZHENG Tian-hui,CHEN Yu-jie.Improvement of aero-engine sealing technology[J].Gas Turbine Experiment and Research,2011,24(4):51-55.(in Chinese)
[3]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.
[4]禄堃.轴流压气机静叶气封间隙流的研究和流道优化[D].北京:清华大学,2008.LU Kun.Research on axial-compressor shrouded stator cavity flows and flow path optimization[D].Beijing:Tsinghua University,2008.(in Chinese)
[5]Gier J,Stubert B,Brouillet B,et al.Interaction of shroud leakage flow and main flow in a three-stage LP turbine[J].Journal of Turbomachinery,2003,127(4):105-116.
[6]马文生,禄堃,顾春伟.压气机静叶气封几何优化与流动分析[J].工程热物理学报,2009,30(8):1288-1290.MA Wen-sheng,LU Kun,GU Chun-wei.Compressor stator seal cavity geometry optimization and flow analysis[J].Journal of Engineering Thermophysics,2009,30(8):1288-1290.(in Chinese)
[7]应银生,马石.叶冠齿数和齿顶间隙对涡轮气动性能的影响[J].航空制造技术,2016,496(1/2):128-131.YING Yin-sheng,MA Shi.Effect of the shroud seal number and the tip clearance on the aerodynamic performance of the turbine[J].Aeronautical Manufacturing Technology,2016,496(1/2):128-131.(in Chinese)
[8]温泉,梁德旺,王可.旋转直管流场的数值模拟[J].南京航空航天大学学报,2000,32(5):539-544.WEN Quan,LIANG De-wang,WANG Ke.Rotary straight pipe field numerical simulation[J].Journal of Nanjing University of Aeronautics&Astronautics,2000,32(5):539-544.
[9]Kuwamura Y,Matsumoto K,Uehara H,et al.Development of new high-performance labyrinth seal using aerodynamic approach[C]∥ASME Turbo Expo 2013:Turbine Technical Conference and Exposition.San Antonio,Texas,US:ASME,2013.
[10]Rhode D L,Allen B F.Measurement and visualization of leakage effects of rounded teeth tips and rub-grooves on stepped labyrinths[J].Journal of Engineering for Gas Turbines&Power,1999,123(3):604-611.
[11]张勃,吉洪湖,杜发青,等.篦齿封严尺寸缩放与气流温度变化对流动与传热影响实验研究[J].推进技术,2016,37(2):304-310.ZHANG Bo,JI Hong-hu,DU Fa-qing,et al.Experimental investigation of scaling and temperature effects on flowing and heat transfer characteristics in labyrinth seals[J].Journal of Propulsion Technology,2016,37(2):304-310.(in Chinese)
[12]塔鲁达纳斯基.非接触密封/间隙密封与迷宫密封的原理和应用[M].李均卿,刁元康,译.北京:机械工业出版社,1986.Trutnovsky K.Berührungsfreie dichtungen:grundlagen und anwendungen der str9mung durch spalte und labyrinth[M].LI Junqing,DIAO Yuan-kang,translated.Beijing:China Machine Press,1986.(in Chinese)
[13]Stocker H L.Determining and improving labyrinth seal performance in current and advanced high performance gas turbines[J].AGARD Conference Proceedings,1978,237:13.
[14]赵海刚,刘振侠.航空发动机篦齿封严特性数值模拟[J].燃气涡轮实验与研究,2010,23(1):26-30.ZHAO Hai-gang,LIU Zhen-xia.Numerical analyses for the performance of straight labyrinth seal of aircraft engine[J].Gas Turbine Experiment and Research,2010,23(1):26-30.(in Chinese)
[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实验[J].航空动力学报,2005,20(3):444-449.WANG Suo-fang,LYU Hai-feng.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]吴丁毅.两类常用篦齿密封和临界特性的分析与比较[J].航空动力学报,1997,12(4):397-400.WU Ding-yi.Two types of commonly used grate tooth seal and critical features analysis and comparison[J].Journal of Aerospace Power,1997,12(4):397-400.(in Chinese)
[17]朱高涛,刘卫华.迷宫密封泄漏量计算方法的分析[J].润滑与密封,2006(4):123-126.ZHU Gao-tao,LIU Wei-hua.Analysis of calculational methods on leakage for labyrinth seals[J].Lubrication Engineering,2006(4):123-126.(in Chinese)