轴承腔内壁与油膜换热的数值模拟与试验
|
摘要
航空发动机后轴承腔内壁与滑油的换热分析是轴承腔热防护结构设计的基础。对航空发动机轴承腔内壁换热模拟试验件开展试验与数值模拟研究,得到了滑油油膜对轴承腔内壁的换热影响。通过测量试验件外壁面、内壁面以及滑油油膜的温度得到了试验件内壁面换热热流密度与换热系数的分布;结合CLSVOF(Coupled Level Set and Volume Of Fluid)油/气两相流以及热-流-固耦合计算方法对试验件进行了换热分析,并将内壁对滑油的局部热流量的计算结果与试验结果进行了对比,结果显示两者在各个工况下均吻合较好。通过将局部换热系数计算值与当地的滑油流动雷诺数Rel进行对比分析,结果显示内壁局部努赛尔数Nuw与Rel的0.7次方成正比关系。另外,对转速对换热的影响进行分析得到Nuw与旋转雷诺数Re_(rot)的0.345次方呈正比关系。
It is necessary to analyze heat transfer between the lubricating oil and the inner wall of the rear bearing chamber in the design of the heat protection structure for an aero-engine.The characteristics of the influence of the inner wall heat transfer from the oil film is obtained through both experiments and numerical simulation.The temperature distribution of the outer wall,inner wall and the oil film is tested to calculate the heat flux and the transfer coefficient.The simulation of the test rig is carried out using fluid-structure coupling with heat transfer,and the CLSVOF(Coupled Level Set and Volume Of Fluid)model is adopted to simulate the gas/oil flow.Comparisons of the local heat flux are then made between the experiments and the numerical simulation under different conditions,and the results show that the simulation results agree well with the experiment data.The relation between the heat coefficient and the local oil film Reynolds number Relis also discussed.The local Nusselt number Nuwnear the wall is directly proportional to 0.7power of local Reynolds number Rel.In addition,analysis of the influence of the rotating speed shows that Nuwis proportional to 0.345 power of the rotary shaft rotational Reynolds number Rerot.
It is necessary to analyze heat transfer between the lubricating oil and the inner wall of the rear bearing chamber in the design of the heat protection structure for an aero-engine.The characteristics of the influence of the inner wall heat transfer from the oil film is obtained through both experiments and numerical simulation.The temperature distribution of the outer wall,inner wall and the oil film is tested to calculate the heat flux and the transfer coefficient.The simulation of the test rig is carried out using fluid-structure coupling with heat transfer,and the CLSVOF(Coupled Level Set and Volume Of Fluid)model is adopted to simulate the gas/oil flow.Comparisons of the local heat flux are then made between the experiments and the numerical simulation under different conditions,and the results show that the simulation results agree well with the experiment data.The relation between the heat coefficient and the local oil film Reynolds number Relis also discussed.The local Nusselt number Nuwnear the wall is directly proportional to 0.7power of local Reynolds number Rel.In addition,analysis of the influence of the rotating speed shows that Nuwis proportional to 0.345 power of the rotary shaft rotational Reynolds number Rerot.
引文
[1]KLINGSPORN M.Advanced transmission and oil system concepts for modern aero-engines:GT2004-53578[R].New York:ASME,2004.
[2]葛治美,韩振兴,张恩和,等.航空发动机轴承腔热分析计算[J].航空动力学报,2005,20(3):483-486.GE Z M,HAN Z X,ZHANG E H,et al.Thermal analysis of aeroengine bearing compartment[J].Journal of Aerospace Power,2005,20(3):483-486(in Chinese).
[3]MICHAEL F.Analytical and numerical simulations of the two-phase flow heat transfer in the vent and scavenge pipes of the CLEAN engine demonstrator[J].Journal of Turbomachinery,2010,132:011008.
[4]GLAHN A,WITTIG S.Two-phase air/oil flow in aero engine bearing chambers:Characterization of oil film flows[J].Journal of Engineering for Gas Turbines and Power,1996,118(3):578-583.
[5]BAI C X,GOSMAN A D.Development of methodology for spray impingement simulation:SAE 950283[R].Warrendale,PA:SAE International,1995.
[6]FARRALL M,HIBBERD S,SIMMONS K.The effect of initial injection conditions on the oil droplet motion in a simplified bearing chamber[J].Journal of Engineering for Gas Turbines and Power,2008,130(1):12501-12507.
[7]SIMMONS K.Numerical study of the two-phase air/oil flow within an aero-engine bearing chamber model using a coupled Lagrangian droplet tracking method[C]//ASME2002Pressure Vessels and Piping Conference.New York:ASME,2002:325-331.
[8]WOLFRAM K,KLAUS D,HANS J B.Influence on the oil split between the offtakes of an aero-engine bearing chamber:GT2012-69412[R].New York:ASME,2012.
[9]WITTIG S,GLAHN A,HIMMELSBACH J.Influence of high rotational speeds on heat transfer and oil film thickness in aero-engine bearing chambers[J].Journal of Engineering for Gas Turbines and Power,1994,116(2):395-401.
[10]GLAHN A,BUSAM S,WITTING S.Local and mean heat transfer coefficients along the internal housing walls of aero engine bearing chambers:GT1997-0261[R].New York:ASME,1997.
[11]BUSAM S,GLAHN A,WITTIG S.Internal bearing chamber wall heat transfer as a function of operating conditions and chamber geometry[J].Journal of Engineering for Gas Turbines and Power,2000,122(2):314-320.
[12]陈薄,陈国定,王涛.考虑油滴变形和二次油滴效应的轴承腔壁面油膜流动分析[J].航空学报,2013,34(8):1980-1989.CHEN B,CHEN G D,WANG T.Flow characteristics analysis of wall oil film with consideration of oil droplet deformation and secondary oil droplet deposition in aeroengine bearing chamber[J].Acta Aeronautica et Astronautica Sinica,2013,34(8):1980-1989(in Chinese).
[13]吕亚国,张美华,刘振侠,等.航空发动机轴承腔油气两相流流动数值研究及验证[J].航空动力学报,2014,29(11):2751-2757.LY G,ZHANG M H,LIU Z X,et al.Numerical study and validation for two-phase flow of oil and gas in aeroengine bearing cavity[J].Journal of Aerospace Power,2014,29(11):2751-2757(in Chinese).
[14]CHONG Z,HU J P,LIU Z X,et al.Application of the ultrasonic oil film thickness measurement system in bearing chambers[J].International Journal of Turo&JetEngines,2013,32(2):159-165.
[15]刘振侠,黄生勤,吕亚国,等.航空发动机润滑系统通用分析软件开发[J].航空动力学报,2007,22(1):12-17.LIU Z X,HUANG S Q,LY G,et al.General analysis software of aeroengine lubrication system design[J].Journal of Aerospace Power,2007,22(1):12-17(in Chinese).
[16]GLAHN A,KURRECK M,WILLMANN M,et al.Feasibility study on oil droplet flow investigations inside aero engine bearing chambers—PDPA technique in combination with numerical approaches[J].Journal of Engineering for Gas Turbines and Power,1996,118(4):749-755.
[17]LIU Z X,ZHAO J Y,HU J P,et al.A numerical model for unsteady oil film motion in aero-engine bearing chamber and experimental verification:GTINDIA 2013-3639[R].New York:ASME,2013.
[18]CHANG Y C,HOU T Y,MERRIMAN B,et al.A level set formulation of eulerian interface capturing methods for incompressible fluid flows[J].Journal of Computational Physics,1996,124(2):449-464.
[19]CHANDRA B,SIMMONS K,PICKERING S,et al.Factors affecting oil removal from an aeroengine bearing chamber:GT2010-22631[R].New York:ASME,2010.
[20]ZHAO J Y,LIU Z X.Numerical and experimental study for unsteady oil film thickness of the rotating cylinder chamber wall[J].Journal of Engineering for Gas Turbines and Power,2015,137(12):122501.
[21]任国哲,刘振侠,赵静宇,等.基于DPM与VOF方法轴承腔内滑油瞬态特性[J].航空计算技术,2016,46(1):11-15.REN G Z,LIU Z X,ZHAO J Y,et al.Motion of wall oil film with consideration of oil-gas coupled heat and mass transfer in bearing chamber[J].Aeronautical Computing Technique,2016,46(1):11-15(in Chinese).
[22]郝毓雅,孙嘉琪,刘振侠,等.轴承腔壁面液膜厚度测量系统的设计与实现[J].航空计算技术,2012,42(6):121-124.HAO Y Y,SUN J Q,LIU Z X,et al.Design and realization of measuring system for film thickness in bearing chamber[J].Aeronautical Computing Technique,2012,42(6):121-124(in Chinese).
[2]葛治美,韩振兴,张恩和,等.航空发动机轴承腔热分析计算[J].航空动力学报,2005,20(3):483-486.GE Z M,HAN Z X,ZHANG E H,et al.Thermal analysis of aeroengine bearing compartment[J].Journal of Aerospace Power,2005,20(3):483-486(in Chinese).
[3]MICHAEL F.Analytical and numerical simulations of the two-phase flow heat transfer in the vent and scavenge pipes of the CLEAN engine demonstrator[J].Journal of Turbomachinery,2010,132:011008.
[4]GLAHN A,WITTIG S.Two-phase air/oil flow in aero engine bearing chambers:Characterization of oil film flows[J].Journal of Engineering for Gas Turbines and Power,1996,118(3):578-583.
[5]BAI C X,GOSMAN A D.Development of methodology for spray impingement simulation:SAE 950283[R].Warrendale,PA:SAE International,1995.
[6]FARRALL M,HIBBERD S,SIMMONS K.The effect of initial injection conditions on the oil droplet motion in a simplified bearing chamber[J].Journal of Engineering for Gas Turbines and Power,2008,130(1):12501-12507.
[7]SIMMONS K.Numerical study of the two-phase air/oil flow within an aero-engine bearing chamber model using a coupled Lagrangian droplet tracking method[C]//ASME2002Pressure Vessels and Piping Conference.New York:ASME,2002:325-331.
[8]WOLFRAM K,KLAUS D,HANS J B.Influence on the oil split between the offtakes of an aero-engine bearing chamber:GT2012-69412[R].New York:ASME,2012.
[9]WITTIG S,GLAHN A,HIMMELSBACH J.Influence of high rotational speeds on heat transfer and oil film thickness in aero-engine bearing chambers[J].Journal of Engineering for Gas Turbines and Power,1994,116(2):395-401.
[10]GLAHN A,BUSAM S,WITTING S.Local and mean heat transfer coefficients along the internal housing walls of aero engine bearing chambers:GT1997-0261[R].New York:ASME,1997.
[11]BUSAM S,GLAHN A,WITTIG S.Internal bearing chamber wall heat transfer as a function of operating conditions and chamber geometry[J].Journal of Engineering for Gas Turbines and Power,2000,122(2):314-320.
[12]陈薄,陈国定,王涛.考虑油滴变形和二次油滴效应的轴承腔壁面油膜流动分析[J].航空学报,2013,34(8):1980-1989.CHEN B,CHEN G D,WANG T.Flow characteristics analysis of wall oil film with consideration of oil droplet deformation and secondary oil droplet deposition in aeroengine bearing chamber[J].Acta Aeronautica et Astronautica Sinica,2013,34(8):1980-1989(in Chinese).
[13]吕亚国,张美华,刘振侠,等.航空发动机轴承腔油气两相流流动数值研究及验证[J].航空动力学报,2014,29(11):2751-2757.LY G,ZHANG M H,LIU Z X,et al.Numerical study and validation for two-phase flow of oil and gas in aeroengine bearing cavity[J].Journal of Aerospace Power,2014,29(11):2751-2757(in Chinese).
[14]CHONG Z,HU J P,LIU Z X,et al.Application of the ultrasonic oil film thickness measurement system in bearing chambers[J].International Journal of Turo&JetEngines,2013,32(2):159-165.
[15]刘振侠,黄生勤,吕亚国,等.航空发动机润滑系统通用分析软件开发[J].航空动力学报,2007,22(1):12-17.LIU Z X,HUANG S Q,LY G,et al.General analysis software of aeroengine lubrication system design[J].Journal of Aerospace Power,2007,22(1):12-17(in Chinese).
[16]GLAHN A,KURRECK M,WILLMANN M,et al.Feasibility study on oil droplet flow investigations inside aero engine bearing chambers—PDPA technique in combination with numerical approaches[J].Journal of Engineering for Gas Turbines and Power,1996,118(4):749-755.
[17]LIU Z X,ZHAO J Y,HU J P,et al.A numerical model for unsteady oil film motion in aero-engine bearing chamber and experimental verification:GTINDIA 2013-3639[R].New York:ASME,2013.
[18]CHANG Y C,HOU T Y,MERRIMAN B,et al.A level set formulation of eulerian interface capturing methods for incompressible fluid flows[J].Journal of Computational Physics,1996,124(2):449-464.
[19]CHANDRA B,SIMMONS K,PICKERING S,et al.Factors affecting oil removal from an aeroengine bearing chamber:GT2010-22631[R].New York:ASME,2010.
[20]ZHAO J Y,LIU Z X.Numerical and experimental study for unsteady oil film thickness of the rotating cylinder chamber wall[J].Journal of Engineering for Gas Turbines and Power,2015,137(12):122501.
[21]任国哲,刘振侠,赵静宇,等.基于DPM与VOF方法轴承腔内滑油瞬态特性[J].航空计算技术,2016,46(1):11-15.REN G Z,LIU Z X,ZHAO J Y,et al.Motion of wall oil film with consideration of oil-gas coupled heat and mass transfer in bearing chamber[J].Aeronautical Computing Technique,2016,46(1):11-15(in Chinese).
[22]郝毓雅,孙嘉琪,刘振侠,等.轴承腔壁面液膜厚度测量系统的设计与实现[J].航空计算技术,2012,42(6):121-124.HAO Y Y,SUN J Q,LIU Z X,et al.Design and realization of measuring system for film thickness in bearing chamber[J].Aeronautical Computing Technique,2012,42(6):121-124(in Chinese).
© 2004-2018 中国地质图书馆版权所有 京ICP备05064691号 京公网安备11010802017129号 地址：北京市海淀区学院路29号 邮编：100083 电话：办公室：(+86 10)66554848；文献借阅、咨询服务、科技查新：66554700 |