跨音转子叶尖泄漏流动的DES研究
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摘要
本文针对某1.5级跨音压气机转子,使用分离涡模拟方法(DES)对其进行了不同工况下的数值模拟,重点关注了叶顶泄漏流动的形态结构、非定常性以及与激波的相互作用。结果表明,分离涡模拟方法能够比雷诺时均方法更好地捕捉泄漏涡的涡系结构和流场细节,且在近失速工况下能够捕获到泄漏流动的非定常现象。泄漏流动的非定常扰动主要发生在在80%叶高以上的叶片压力面侧,对转子总体性能产生了影响。泄漏涡通过激波后结构出现了较大改变,泄漏涡和激波作用之后导致涡破碎可能是叶顶流动中非定常性的根本来源。
The DES method was adopted in the numerical investigations of the transonic rotor of a 1.5-stage compressor at different working conditions.The detailed structures of the tip leakage flow,the unsteadiness characteristics and the interaction with the shock were mainly focused.The DES results have a better resolution for the vortex structure and detailed flow field of the tip leakage flow than RANS results.Unsteadiness at near stall point was successfully captured by DES method.Fluctuations in the tip leakage flow were located at the pressure side of the blade above 80% span,which have a large impact on the overall performance of the rotor.An abrupt change was found in the tip leakage vortex after passing through the shock.The vortex breakdown resulted from the interaction process may be the fundamental cause of the unsteadiness in the tip flow field.
The DES method was adopted in the numerical investigations of the transonic rotor of a 1.5-stage compressor at different working conditions.The detailed structures of the tip leakage flow,the unsteadiness characteristics and the interaction with the shock were mainly focused.The DES results have a better resolution for the vortex structure and detailed flow field of the tip leakage flow than RANS results.Unsteadiness at near stall point was successfully captured by DES method.Fluctuations in the tip leakage flow were located at the pressure side of the blade above 80% span,which have a large impact on the overall performance of the rotor.An abrupt change was found in the tip leakage vortex after passing through the shock.The vortex breakdown resulted from the interaction process may be the fundamental cause of the unsteadiness in the tip flow field.
引文
[1]Denton J D.Loss Mechanisms in Turbomachines[C]//ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition.American Society of Mechanical Engineers,1993:V002T14A001
[2]Vo H D.Role of Tip Clearance Flow on Axial Compressor Stability[D].Massachusetts Institute of Technology,2002
[3]Tahara N,Nakajima T,Kurosaki M et al.Active Stall Control with Practicable Stall Prediction System Using Auto-correlation Coefficient[C]//37th Joint Propulsion Conference and Exhibit.2001:3623
[4]Muller M W,Schiffer H P,Hah C.Effect of Circumferential Grooves on the Aerodynamic Performance of an Axial Single-stage Transonic Compressor[C]//ASME Turbo Expo 2007:Power for Land,Sea,and Air.American Society of Mechanical Engineers,2007:115-124
[5]Legras G,Gourdain N,Trebinjac I.Numerical Analysis of the Tip Leakage Flow Field in a Transonic Axial Compressor with Circumferential Casing Treatment[J].Journal of Thermal Science,2010,19(3):198-205
[6]邓向阳,张宏武,黄伟光.低速轴流压气机中工况变化对动叶顶部泄漏流波动频率的影响[J].工程热物理学报,2005,26(6):938-940DENG Xiangyang,ZHANG Hongwu,HUANG Weiguang.Effects of Operating Condition on the Frequency Characteristic of Rotor Tip Leakage Flow in a Low-speed Axial Compressor[J].Journal of Engineering Thermophysics,2005,26(6):938-940
[7]Hoying D A,Tan C S,Vo H D et al.Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception[C]//ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition.American Society of Mechanical Engineers,1998:V001T01A138
[8]Vo H D,Tan C S,Greitzer E M.Criteria for Spike Initiated Rotating Stall[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2008,130(1):11023
[9]Deppe,Saathoff,Stark.Discussion:Criteria for Spike Initiated Rotating Stall[J].Journal of Turbomachinery,2008
[10]Yamada K,Kikuta H,Iwakiri K I et al.An Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor[C]//ASME Turbo Expo 2012:Turbine Technical Conference and Exposition,2013:2663-2675
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[12]张燕峰,楚武利,卢新根.跨声速轴流压气机近失速状态的间隙泄漏流流动特性[J].航空动力学报,2008,23(7):1293-1298ZHANG Yanfeng,CHU Wuli,LU Xingen.Numerical Simulation of the Flow Characteristic of Tip Leakage Flow in a Transonic Axial-flow Compressor at Near Stall Condition[J].Journal of Aerospace Power,2008,23(7):1293-1298
[13]Biela C,Muller M W,Schiffer H P et al.Unsteady Pressure Measurement in a Single Stage Axial Transonic Compressor Near the Stability Limit[C]//ASME Turbo Expo,2008:157-165
[14]Du J,Lin F,Chen J et al.Flow Structures in the Tip Region for a Transonic Compressor Rotor[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2013,135(3):31012
[15]Puterbaugh S,Brendel M.Tip Clearance Flow-shock Interaction in a Transonic Compressor Rotor[J].Journal of propulsion and power,New York,NY:American Institute of Aeronautics and Astronautics,c1985-,1997,13(1):24-30
[16]Yamada K,Furukawa M,Nakano T et al.Unsteady Three-dimensional Flow Phenomena Due to Breakdown of Tip Leakage Vortex in a Transonic Axial Compressor Rotor[J].ASME Paper No.GT2004-53745,2004
[17]Hofmann W,Ballman J.Some Aspects of Tip Vortex Behavior in a Transonic Turbocompressor[C]//ISABE,2003:745-753
[18]Ottavy X,Courtiade N,Gourdain N.Experimental and Computational Methods for Flow Investigation in Highspeed Multistage Compressor[J].African Studies Review,2012,28(6):1141-1155
[19]Iim H,Chen X Y,Zha G.Detached-Eddy Simulation of Rotating Stall Inception for a Full-annulus Transonic Rotor[J].Journal of Propulsion&Power,2013,28(4):782-798
[20]Liu Y,Yu X,Liu B.Turbulence Models Assessment for Large-scale Tip Vortices in an Axial Compressor Rotor[J].Journal of Propulsion and Power,2008,24(1):15-25
[21]Spalart P R,Jou W H,Strelets M et al.Comments on the Feasibility of LES for Wings,and on a Hybrid RANS/LES Approach[C]//Advances in DNS/LES,1997
[22]顾春伟,奉凡,李雪松,等.DES模型在压气机亚音转子中的应用探讨[J].工程热物理学报,2008,29(6):951-956GU Chunwei,FENG Fan,LI Xuesong,et al.Application of Detached Eddy Simulation in Subsonic Compressor Rotor[J].Journal of Engineering Thermophysics,2008,29(6):951-956
[23]李雪松,奉凡,顾春伟.静动干涉流动的分离涡模拟研究[J].工程热物理学报,2009,30(6):953-956LI Xuesong,FENG Fan,GU Chunwei.Detached Eddy Simulation for the Stator-rotor Interaction[J].Journal of Engineering Thermophysics,2009,30(6):953-956
[24]Lin D,Su X,Yuan X.DDES Analysis of Wake Vortex Related Unsteadiness and Losses in the Environment of High-pressure Turbine Stage[C]//ASME Turbo Expo2017:Turbomachinery Technical Conference and Exposition,2017:V02DT46A022
[25]Yamada K,Furukawa M,Tamura Y et al.Large-scale Detached-eddy Simulation Analysis of Stall Inception Process in a Multistage Axial Flow Compressor[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2017,139(7):71002
[26]Riera W,Castillon L,Marty J et al.Inlet Condition Effects on the Tip Clearance Flow with Zonal Detached Eddy Simulation[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2014,136(4):41018
[27]Riera W,Marty J,Castillon L et al.Zonal Detached-eddy Simulation Applied to the Tip-clearance Flow in an Axial Compressor[J].AIAA Journal,American Institute of Aeronautics and Astronautics,2016,54(8):2377-2391
[2]Vo H D.Role of Tip Clearance Flow on Axial Compressor Stability[D].Massachusetts Institute of Technology,2002
[3]Tahara N,Nakajima T,Kurosaki M et al.Active Stall Control with Practicable Stall Prediction System Using Auto-correlation Coefficient[C]//37th Joint Propulsion Conference and Exhibit.2001:3623
[4]Muller M W,Schiffer H P,Hah C.Effect of Circumferential Grooves on the Aerodynamic Performance of an Axial Single-stage Transonic Compressor[C]//ASME Turbo Expo 2007:Power for Land,Sea,and Air.American Society of Mechanical Engineers,2007:115-124
[5]Legras G,Gourdain N,Trebinjac I.Numerical Analysis of the Tip Leakage Flow Field in a Transonic Axial Compressor with Circumferential Casing Treatment[J].Journal of Thermal Science,2010,19(3):198-205
[6]邓向阳,张宏武,黄伟光.低速轴流压气机中工况变化对动叶顶部泄漏流波动频率的影响[J].工程热物理学报,2005,26(6):938-940DENG Xiangyang,ZHANG Hongwu,HUANG Weiguang.Effects of Operating Condition on the Frequency Characteristic of Rotor Tip Leakage Flow in a Low-speed Axial Compressor[J].Journal of Engineering Thermophysics,2005,26(6):938-940
[7]Hoying D A,Tan C S,Vo H D et al.Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception[C]//ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition.American Society of Mechanical Engineers,1998:V001T01A138
[8]Vo H D,Tan C S,Greitzer E M.Criteria for Spike Initiated Rotating Stall[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2008,130(1):11023
[9]Deppe,Saathoff,Stark.Discussion:Criteria for Spike Initiated Rotating Stall[J].Journal of Turbomachinery,2008
[10]Yamada K,Kikuta H,Iwakiri K I et al.An Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor[C]//ASME Turbo Expo 2012:Turbine Technical Conference and Exposition,2013:2663-2675
[11]桂幸民,王同庆,于清,等.跨音压气机转子叶尖流场试验与分析[J].工程热物理学报,1998,19(5):553-558GUI Xingmin,WANG Tongqing,YU Qing,et al.Investigation on the Tip Clearance Flow Field in a Transonic Compressor Rotor[J].Journal of Engineering Thermophysics,1998,19(5):553-558
[12]张燕峰,楚武利,卢新根.跨声速轴流压气机近失速状态的间隙泄漏流流动特性[J].航空动力学报,2008,23(7):1293-1298ZHANG Yanfeng,CHU Wuli,LU Xingen.Numerical Simulation of the Flow Characteristic of Tip Leakage Flow in a Transonic Axial-flow Compressor at Near Stall Condition[J].Journal of Aerospace Power,2008,23(7):1293-1298
[13]Biela C,Muller M W,Schiffer H P et al.Unsteady Pressure Measurement in a Single Stage Axial Transonic Compressor Near the Stability Limit[C]//ASME Turbo Expo,2008:157-165
[14]Du J,Lin F,Chen J et al.Flow Structures in the Tip Region for a Transonic Compressor Rotor[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2013,135(3):31012
[15]Puterbaugh S,Brendel M.Tip Clearance Flow-shock Interaction in a Transonic Compressor Rotor[J].Journal of propulsion and power,New York,NY:American Institute of Aeronautics and Astronautics,c1985-,1997,13(1):24-30
[16]Yamada K,Furukawa M,Nakano T et al.Unsteady Three-dimensional Flow Phenomena Due to Breakdown of Tip Leakage Vortex in a Transonic Axial Compressor Rotor[J].ASME Paper No.GT2004-53745,2004
[17]Hofmann W,Ballman J.Some Aspects of Tip Vortex Behavior in a Transonic Turbocompressor[C]//ISABE,2003:745-753
[18]Ottavy X,Courtiade N,Gourdain N.Experimental and Computational Methods for Flow Investigation in Highspeed Multistage Compressor[J].African Studies Review,2012,28(6):1141-1155
[19]Iim H,Chen X Y,Zha G.Detached-Eddy Simulation of Rotating Stall Inception for a Full-annulus Transonic Rotor[J].Journal of Propulsion&Power,2013,28(4):782-798
[20]Liu Y,Yu X,Liu B.Turbulence Models Assessment for Large-scale Tip Vortices in an Axial Compressor Rotor[J].Journal of Propulsion and Power,2008,24(1):15-25
[21]Spalart P R,Jou W H,Strelets M et al.Comments on the Feasibility of LES for Wings,and on a Hybrid RANS/LES Approach[C]//Advances in DNS/LES,1997
[22]顾春伟,奉凡,李雪松,等.DES模型在压气机亚音转子中的应用探讨[J].工程热物理学报,2008,29(6):951-956GU Chunwei,FENG Fan,LI Xuesong,et al.Application of Detached Eddy Simulation in Subsonic Compressor Rotor[J].Journal of Engineering Thermophysics,2008,29(6):951-956
[23]李雪松,奉凡,顾春伟.静动干涉流动的分离涡模拟研究[J].工程热物理学报,2009,30(6):953-956LI Xuesong,FENG Fan,GU Chunwei.Detached Eddy Simulation for the Stator-rotor Interaction[J].Journal of Engineering Thermophysics,2009,30(6):953-956
[24]Lin D,Su X,Yuan X.DDES Analysis of Wake Vortex Related Unsteadiness and Losses in the Environment of High-pressure Turbine Stage[C]//ASME Turbo Expo2017:Turbomachinery Technical Conference and Exposition,2017:V02DT46A022
[25]Yamada K,Furukawa M,Tamura Y et al.Large-scale Detached-eddy Simulation Analysis of Stall Inception Process in a Multistage Axial Flow Compressor[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2017,139(7):71002
[26]Riera W,Castillon L,Marty J et al.Inlet Condition Effects on the Tip Clearance Flow with Zonal Detached Eddy Simulation[J].Journal of Turbomachinery,American Society of Mechanical Engineers,2014,136(4):41018
[27]Riera W,Marty J,Castillon L et al.Zonal Detached-eddy Simulation Applied to the Tip-clearance Flow in an Axial Compressor[J].AIAA Journal,American Institute of Aeronautics and Astronautics,2016,54(8):2377-2391
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