航空发动机组合式弹性片金属密封环结构密封特性研究
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摘要
为研究航空发动机组合式弹性片金属密封环结构的密封特性,设计和搭建了弹性片结构密封特性实验平台,研究腔室气体压力、弹性片压缩量对弹性片密封结构气体泄漏率和泄漏面积的影响规律。定量描述了气体泄漏量与弹性片压缩量及腔室气体压力的关系,分析了其密封机理。研究结果表明:气体泄漏率随腔室压力增大而线性增大;腔室气体压力使弹性片结构有一定的密封效果,压力越大密封效果越好,同时压力越大弹性片压缩量的增大对密封性的改善效果不显著;在压缩量较小或者腔室压力很低的条件下,接触泄漏和通道泄漏共存;当压缩量增大到0.80mm和腔室压力增大到0.40MPa时,继续增大压缩量或腔室压力对减小泄漏面积作用不大,泄漏面积会稳定在169mm~2,即为通道泄漏面积。
In order to study the sealing characteristics of composite elastic metal sealing rings used in an aeroengine,an experimental platform for the sealing characteristics of elastic metal sealing rings was designed and built. Effects of gas pressure in the chamber and compression deformation of the elastic metal rings on the leakage rate and leakage area were studied. A quantitative description of the amount of leakage with the compression deformation and the chamber pressure was established,the sealing mechanism was analyzed. By the results of this experiment it is concluded that the leakage rate increases linearly with the increase of the chamber pressure. The pressure of the chamber makes the elastic metal sealing rings establish a certain sealing effect. The higher the pressure,the better the sealing effects. While the greater the pressure,the increasing of the compression deformation of elastic metal rings has no significant effects on the sealing performance. When the compression deformation is smaller or gas pressure in the chamber is lower,the contact leakage and channel leakage coexistence. When the compression deformation increases to 0.80 mm and the chamber pressure increases to0.40 MPa,the increase of the compression or the chamber pressure has little effect on reducing the leakage area,and the leakage area will be stable at 169 mm2,which is channel leakage area.
In order to study the sealing characteristics of composite elastic metal sealing rings used in an aeroengine,an experimental platform for the sealing characteristics of elastic metal sealing rings was designed and built. Effects of gas pressure in the chamber and compression deformation of the elastic metal rings on the leakage rate and leakage area were studied. A quantitative description of the amount of leakage with the compression deformation and the chamber pressure was established,the sealing mechanism was analyzed. By the results of this experiment it is concluded that the leakage rate increases linearly with the increase of the chamber pressure. The pressure of the chamber makes the elastic metal sealing rings establish a certain sealing effect. The higher the pressure,the better the sealing effects. While the greater the pressure,the increasing of the compression deformation of elastic metal rings has no significant effects on the sealing performance. When the compression deformation is smaller or gas pressure in the chamber is lower,the contact leakage and channel leakage coexistence. When the compression deformation increases to 0.80 mm and the chamber pressure increases to0.40 MPa,the increase of the compression or the chamber pressure has little effect on reducing the leakage area,and the leakage area will be stable at 169 mm2,which is channel leakage area.
引文
[1]李钰洁,刘永葆,贺星.间隙变化对新型涡轮密封气动性能影响的数值分析[J].推进技术,2015,36(8):1179-1185.(LI Yu-jie,LIU Yong-bao,HE Xing.Numerical Simulation for Effect of Clearance Change of a Novel Seal on Aerodynamic Performance of Gas Turbine[J].Journal of Propulsion Technology,2015,36(8):1179-1185.)
[2]李钰洁,刘永葆,贺星.基于气动性能优化的涡轮叶顶新型密封构型研究[J].推进技术,2015,36(5):696-702.(LI Yu-jie,LIU Yong-bao,HE Xing.Study Optimization Research on a Novel Turbine Blade Tip Seal Configuration Based on Aerodynamic Performance[J].Journal of Propulsion Technology,2015,36(5):696-702.)
[3]徐旭,康顺,谭春青,等.涡喷发动机涡轮密封舱小气路流场数值计算[J].推进技术,2000,21(2):29-32.(XU Xu,KANG Shun,TAN Chun-qing,et al.Numerical Simulation on Viscous Flow in the Secondary Flow Path of a Turbine Sealed Cabin[J].Journal of Propulsion Technology,2000,21(2):29-32.)
[4]李伟,乔渭阳,许开富,等.涡轮叶尖迷宫式密封对泄漏流场影响的数值模拟[J].推进技术,2009,30(1):88-94.(LI Wei,QIAO Wei-yang,XU Kai-fu,et al.Numerical Simulation of Labyrinth Seal on Tip Leakage Flow in Partially and Fully Shrouded Axial Turbine[J].Journal of Propulsion Technology,2009,30(1):88-94.)
[5]胡广阳.航空发动机密封技术研究[J].航空发动机,2012,38(3):1-4.
[6]李玉婷,廖日东,辛婷,等.低温U形金属密封环密封性能有限元分析[J].润滑与密封.2014,39(7):60-66.
[7]刘艳梅,孙扬,宋鸿达.某涡喷发动机密封环研制[J].推进技术,1999,20(6):45-47.(LIU Yan-mei,SUN Yang,SONG Hong-da.Study of Seal Ring of Turbojet Engine[J].Journal of Propulsion Technology,1999,20(6):45-47.)
[8]黄迷梅.液压气动密封与泄漏防治[M].北京:机械工业出版社,2003.
[9]近森徳重,河原由夫共.密封装置[M].东京:幸书房,1975.
[10]Müller H K,Nau B S.Fluid Sealing Technology:Principles and Applications[M].New York:Marcel Dekker,Inc.,1998.
[11]近森德重.密封元件O形密封圈[M].北京:机械工业出版社,1976.
[12]合肥通用机械研究所高压密封课程组.金属O形环基础试验[J].化工与通用机械,1978,(2):19-25.
[13]合肥通用机械研究所高压密封课程组.高温高压金属O形环密封试验研究[J].化工与通用机械,1978,(2):14-18.
[14]彭向和,高芝晖,曾祥国.O形密封环的弹塑性大变形和循环松弛分析[J].重庆大学学报:自然科学版,1998,21(2):46-50.
[15]余伟炜,蔡力勋,叶裕明,等.Inconel718金属O形环回弹特性研究[J].工程力学,2006,23(6):142-147.
[16]李亚明,文联奎,赵正修.不锈钢O形环垫的密封性能试验研究[J].中国石油大学学报自然科学版,1994,18(6):80-85.
[17]蔡仁良.流体密封技术:原理与工程应用[M].北京:化学工业出版社,2013.
[18]Tsujikawa H,Maruoka S,Koeda M,et al.Preliminary Studies on Large Metal-Sealed Gate Valves for the International Thermonuclear Experimental Reactor(ITER)[J].Vacuum,1996,47(6):639-646.
[19]Liu Y,Zhou K,Huang W F,et al.Numerical and Experimental Analysis of the Reusability of Spring Energized Metal C Rings[J].Science China Technological Sciences,2014,57(8):1670-1676.
[20]左国,郝守信,尹小龙.先进压水堆C形环研究[J].核动力工程,2002,23(2):107-112.
[21]吕英,伊松年,朱丽平,等.制动管系用E形双面主动密封法兰密封圈的研制[J].铁道车辆,2009,47(10):11-14.
[22]陈晔,顾伯勤,冯秀.Ω形密封环的应力分析[J].南京工业大学学报(自科版),2002,24(6):44-47.
[23]顾雪东.高压换热器的Ω形环密封结构[J].压力容器,2000,17(6):25-26.
[24]邢敏杰.航空发动机中W形金属密封环密封性能及泄漏研究[D].北京:北京理工大学,2015.
[25]龚雪婷.航空发动机用W形金属密封环特性研究[D].北京:北京化工大学,2011.
[26]Sarawate N,Wolfe C,Sezer I,et al.Characterization of Metallic W-Seals for Inner to Outer Shroud Sealing in Industrial Gas Turbines[C].Copenhagen:Turbine Technical Conference and Exposition.American Society of Mechanical Engineers,2012:1855-1862.
[2]李钰洁,刘永葆,贺星.基于气动性能优化的涡轮叶顶新型密封构型研究[J].推进技术,2015,36(5):696-702.(LI Yu-jie,LIU Yong-bao,HE Xing.Study Optimization Research on a Novel Turbine Blade Tip Seal Configuration Based on Aerodynamic Performance[J].Journal of Propulsion Technology,2015,36(5):696-702.)
[3]徐旭,康顺,谭春青,等.涡喷发动机涡轮密封舱小气路流场数值计算[J].推进技术,2000,21(2):29-32.(XU Xu,KANG Shun,TAN Chun-qing,et al.Numerical Simulation on Viscous Flow in the Secondary Flow Path of a Turbine Sealed Cabin[J].Journal of Propulsion Technology,2000,21(2):29-32.)
[4]李伟,乔渭阳,许开富,等.涡轮叶尖迷宫式密封对泄漏流场影响的数值模拟[J].推进技术,2009,30(1):88-94.(LI Wei,QIAO Wei-yang,XU Kai-fu,et al.Numerical Simulation of Labyrinth Seal on Tip Leakage Flow in Partially and Fully Shrouded Axial Turbine[J].Journal of Propulsion Technology,2009,30(1):88-94.)
[5]胡广阳.航空发动机密封技术研究[J].航空发动机,2012,38(3):1-4.
[6]李玉婷,廖日东,辛婷,等.低温U形金属密封环密封性能有限元分析[J].润滑与密封.2014,39(7):60-66.
[7]刘艳梅,孙扬,宋鸿达.某涡喷发动机密封环研制[J].推进技术,1999,20(6):45-47.(LIU Yan-mei,SUN Yang,SONG Hong-da.Study of Seal Ring of Turbojet Engine[J].Journal of Propulsion Technology,1999,20(6):45-47.)
[8]黄迷梅.液压气动密封与泄漏防治[M].北京:机械工业出版社,2003.
[9]近森徳重,河原由夫共.密封装置[M].东京:幸书房,1975.
[10]Müller H K,Nau B S.Fluid Sealing Technology:Principles and Applications[M].New York:Marcel Dekker,Inc.,1998.
[11]近森德重.密封元件O形密封圈[M].北京:机械工业出版社,1976.
[12]合肥通用机械研究所高压密封课程组.金属O形环基础试验[J].化工与通用机械,1978,(2):19-25.
[13]合肥通用机械研究所高压密封课程组.高温高压金属O形环密封试验研究[J].化工与通用机械,1978,(2):14-18.
[14]彭向和,高芝晖,曾祥国.O形密封环的弹塑性大变形和循环松弛分析[J].重庆大学学报:自然科学版,1998,21(2):46-50.
[15]余伟炜,蔡力勋,叶裕明,等.Inconel718金属O形环回弹特性研究[J].工程力学,2006,23(6):142-147.
[16]李亚明,文联奎,赵正修.不锈钢O形环垫的密封性能试验研究[J].中国石油大学学报自然科学版,1994,18(6):80-85.
[17]蔡仁良.流体密封技术:原理与工程应用[M].北京:化学工业出版社,2013.
[18]Tsujikawa H,Maruoka S,Koeda M,et al.Preliminary Studies on Large Metal-Sealed Gate Valves for the International Thermonuclear Experimental Reactor(ITER)[J].Vacuum,1996,47(6):639-646.
[19]Liu Y,Zhou K,Huang W F,et al.Numerical and Experimental Analysis of the Reusability of Spring Energized Metal C Rings[J].Science China Technological Sciences,2014,57(8):1670-1676.
[20]左国,郝守信,尹小龙.先进压水堆C形环研究[J].核动力工程,2002,23(2):107-112.
[21]吕英,伊松年,朱丽平,等.制动管系用E形双面主动密封法兰密封圈的研制[J].铁道车辆,2009,47(10):11-14.
[22]陈晔,顾伯勤,冯秀.Ω形密封环的应力分析[J].南京工业大学学报(自科版),2002,24(6):44-47.
[23]顾雪东.高压换热器的Ω形环密封结构[J].压力容器,2000,17(6):25-26.
[24]邢敏杰.航空发动机中W形金属密封环密封性能及泄漏研究[D].北京:北京理工大学,2015.
[25]龚雪婷.航空发动机用W形金属密封环特性研究[D].北京:北京化工大学,2011.
[26]Sarawate N,Wolfe C,Sezer I,et al.Characterization of Metallic W-Seals for Inner to Outer Shroud Sealing in Industrial Gas Turbines[C].Copenhagen:Turbine Technical Conference and Exposition.American Society of Mechanical Engineers,2012:1855-1862.