用于压气机流动计算的3种模型比较
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摘要
为了更好地对压气机流动进行模拟,在课题组自行开发的结构化有限体积解算器上实现了用于压气机流场计算的混合平面法、谐波平衡法及相滞后法.以NASA Stage 35为例,对3种方法的计算结果进行了比较分析.结果表明:相滞后法的计算精度最高,混合平面法的计算精度最低;相滞后法与半环的双时间推进法结果相近,计算速度提高了20倍;相比混合平面法,谐波平衡法能准确地模拟动静叶间的非定常干涉及进出口参数变化;在谐波阶数达到5阶后,谐波平衡法计算得到的结果不随阶数变化,且与相滞后法的结果基本吻合;混合平面法的计算效率远高于另外两种方法,相滞后法与谐波平衡法在谐波阶数为5阶时的计算效率相当.
In order to simulate the flow of compressor better,mixing plane method,harmonic balance method and phase lag method for CFD of compressor internal flow were implemented into an in-house finite volume code.Taking NASA Stage 35 compressor model as an example,results of three methods were compared with each other.Result indicates that,phase lag method ranks highest in terms of accuracy and mixing plane method ranks lowest;the result of phase lag method is as accurate as the result of half annulus simulation of the flow with the dual time stepping method,and a factor of 20speed-up could be achieved;compared with mixing plane method,harmonic balance method can simulate unsteady interference between rotor and stator and global parameters variation in inlet and outlet accurately;when the harmonic order is set more than or equal to 5,the result of harmonic method does not vary with the harmonic order and matches well with the result of phase lag method;computational efficiency of mixing plane is much higher than the other two methods,computational efficiency of phase lag method is nearly equal to harmonic balance method with a harmonic order of 5.
In order to simulate the flow of compressor better,mixing plane method,harmonic balance method and phase lag method for CFD of compressor internal flow were implemented into an in-house finite volume code.Taking NASA Stage 35 compressor model as an example,results of three methods were compared with each other.Result indicates that,phase lag method ranks highest in terms of accuracy and mixing plane method ranks lowest;the result of phase lag method is as accurate as the result of half annulus simulation of the flow with the dual time stepping method,and a factor of 20speed-up could be achieved;compared with mixing plane method,harmonic balance method can simulate unsteady interference between rotor and stator and global parameters variation in inlet and outlet accurately;when the harmonic order is set more than or equal to 5,the result of harmonic method does not vary with the harmonic order and matches well with the result of phase lag method;computational efficiency of mixing plane is much higher than the other two methods,computational efficiency of phase lag method is nearly equal to harmonic balance method with a harmonic order of 5.
引文
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[18]薛亮,韩万金,黄家骅,等.单级压气机气动优化设计[J].推进技术,2009,30(4):419-424.XUE Liang,HAN Wanjin,HUANG Jiahua,et al.Aerodynamic optimization design of a single stage compressor[J].Journal of Propulsion Technology,2009,30(4):419-424.(in Chinese)
[2]He L.An Euler solution for unsteady flows around oscillating blades[J].Journal of Turbomachinery,1990,112(4):714-722.
[3]He L,Ning W.Efficient approach for analysis of unsteady viscous flows in turbomachines[J].AIAA Journal,1998,36(11):2005-2012.
[4]Hall K C,Thomas J P,Clark W S.Computation of unsteady nonlinear flows in cascades using a harmonic balance technique[R].Grenoble:The 9th International Symposium on Unsteady Aerodynamics,Aeroacoustics,and Aeroelasticity of Turbomachines,2000.
[5]Gopinath A,Jameson A.Time spectral method for periodic unsteady computations over two-and three-dimensional bdies[R].AIAA-2005-1220,2005.
[6]张健.跨声速多级轴流压气机三维流场及气动性能数值模拟研究[D].四川绵阳:中国空气动力研究与发展中心,2014.ZHANG Jian.Research on numerical simulation of 3Dflow field and aerodynamic performance of transonic multistage axial compressor[D].Mianyang Sichuan:China Aerodynamic Research and Development Center,2014.(in Chinese)
[7]王雷,刘波.非线性谐波法在对转压气机中的校验分析[J].航空动力学报,2012,27(7):1448-1455.WANG Lei,LIU Bo.Validation of nonlinear harmonic method in dual-stage counter-rotating compressor[J].Journal of Aerospace Power,2012,27(7):1448-1455.(in Chinese)
[8]刘波,王雷,黄建.非线性谐波法在双级对转压气机中的进一步校验[J].航空动力学报,2013,28(6):1333-1341.LIU Bo,WANG Lei,HUANG Jian.Further validation of nonlinear harmonic method in dual-stage counter-rotating compressor[J].Journal of Aerospace Power,2013,28(6):1333-1341.(in Chinese)
[9]马灿,苏欣荣,袁新.用于非定常流动的谐波平衡方法研究[J].工程热物理学报,2015,36(4):739-743.MA Can,SU Xinrong,YUAN Xin.Research on harmonic balance method for unsteady flow simulation[J].Journal of Engineering Thermophysics,2015,36(4):739-743.(in Chinese)
[10]杜鹏程.叶轮机转静非定常流动建模技术研究[D].北京:北京航空航天大学,2015.DU Pengcheng.Investigation of the modeling methodologies for the rotor-stator unsteady flow interactions in turbomachinery[D].Beingjing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese)
[11]Biesinger T,Cornelius C,Rube C,et al.Unsteady CFD methods in a commercial solver for turbomachinery applications[R].ASME Paper GT2010-22762,2010.
[12]NUMECA International.User manual fineTM/turbo v9.0flow integated environment[R].Brussels:NUMECA International,2013.
[13]Gerolymos G A,Michon G J,Neubauer J.Analysis and application of chorochronic periodicity in turbomachinery rotor/stator interaction computations[J].Journal of Propulsion and Power,2002,18(6):1139-1152.
[14]Erdos J I,Alzner E,McNally W,Numerical solution of periodic transonic flow through a fan stage[J].AIAA Journal,1977,15(11):1559-1568.
[15]牟斌,肖中云,周铸,等.直升机旋翼悬停流场的粘性数值模拟[J].空气动力学学报,2009,27(5):582-585.MOU Bin,XIAO Zhongyun,ZHOU Zhu,et al.Numerical simulation of viscous flow-fields around helicopter rotor[J].Journal of Aerodynamic,2009,27(5):582-585.(in Chinese)
[16]肖中云.旋翼流场数值模拟方法研究[D].四川绵阳:中国空气动力研究与发展中心,2007.XIAO Zhongyun.Investigation of computation modeling techiques for rotor flow fields[D].Mianyang Sichuan:China Aerodynamic Research and Development Center,2007.(in Chinese)
[17]Reid L,Moore R D.Performance of a single-stage axialflow transonic compressor with rotor and stator aspect ratios of 1.19and 1.26,respectively,and with design pressure ratio of 1.82[R].NASA TP-1338,1978.
[18]薛亮,韩万金,黄家骅,等.单级压气机气动优化设计[J].推进技术,2009,30(4):419-424.XUE Liang,HAN Wanjin,HUANG Jiahua,et al.Aerodynamic optimization design of a single stage compressor[J].Journal of Propulsion Technology,2009,30(4):419-424.(in Chinese)