基于POD方法的跨声速轴流压气机转子叶顶间隙流场分析

傅珏; 杨波; 钟芳源

doi:10.13224/j.cnki.jasp.2019.09.022

基于POD方法的跨声速轴流压气机转子叶顶间隙流场分析

doi: 10.13224/j.cnki.jasp.2019.09.022

上海交通大学机械与动力工程学院,上海 200240

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出版历程
- 收稿日期: 2019-01-26
- 刊出日期: 2019-09-28

Analysis of transonic axial compressor tip clearance flow field with POD method

摘要

摘要: 以跨声速轴流压气机转子NASA Rotor 36为对象,研究了叶顶间隙流场的非定常流动特性。在数值模拟结果的基础上,采用本征正交分解(POD)方法获取POD模态和时间系数分布规律,进一步分析了近失速工况下叶顶间隙流场的流动特性。结果表明:在近失速工况下,叶顶间隙流场的主导频率为叶顶泄漏涡频率,约为0.6倍转子通过频率;能量较高的POD模态决定了叶顶泄漏涡的波动频率和幅值,低能量的高阶涡则影响流场的细微结构;同时发现,前5阶POD模态就可以很好地重构流场,这为低阶模型的应用提供了一定的理论指导。
- 本征正交分解(POD) /
- 跨声速轴流压气机 /
- 叶顶间隙流 /
- 非定常流动 /
- 本征正交分解(POD)模态
Abstract: The unsteady flow phenomenon of a transonic axial compressor NASA Rotor 36 was investigated. Based on the unsteady simulation results, proper orthogonal decomposition (POD) modes and time coefficients were obtained with POD method, and the flow characteristics of the tip clearance flow field at near stall conditions were further analyzed. Results showed that: at near stall condition, the dominant frequency of tip clearance flow field was the tip leakage vortex frequency, about 0.6 times blade passing frequency; the POD mode with higher energy determined the fluctuation frequency and amplitude of tip leakage vortex, and the POD mode with lower energy determined the fine structure of the flow field; the first 5 POD modes reconstructed the flow field very well, providing a theoretical guidance for the establishment of the low-order model.
- proper orthogonal decomposition(POD) /
- transonic axial compressor /
- tip clearance flow /
- unsteady flow /
- proper orthogonal decomposition(POD) mode

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参考文献(16)

[1]	LUMLEY J L.The structure of inhomogeneous turbulent flows［C］∥Atmospheric turbulence and radio wave propagation.Moscow:Nauka,1967,166-178.
[2]	AUBRY N,HOLMES P,LUMLEY J L,et al.The dynamics of coherent structures in the wall region of a turbulent boundary layer［J］.Journal of Fluid Mechanics,1988,192:115-173.
[3]	MA X,KARNIADAKIS G E.A low-dimensional model for simulating three-dimensional cylinder flow［J］.Journal of Fluid Mechanics,2002,458:181-190.
[4]	HALL K C,THOMAS J P,DOWELL E H.Proper orthogonal decomposition technique for transonic unsteady aerodynamic flows［J］.AIAA Journal,2015,38(10):1853-1862.
[5]	SIEGEL S,COHEN K,JRGEN SEIDEL,et al.Short time proper orthogonal decomposition for state estimation of transient flow fields［R］.AIAA 2005-296,2005.
[6]	LUO J,TANG X,DUAN Y,et al.An iterative inverse design method of turbomachinery blades by using proper orthogonal decomposition［R］.ASME Paper 2015-GT-42876,2015.
[7]	王掩刚,陈俊旭,先松川.基于POD方法的二维方柱低雷诺数绕流流场分析研究［J］.西北工业大学学报,2014,32(4):612-617.WANG Yangang,CHEN Junxu,XIAN Songchuan.Analysis of square cylinder unsteady flow at low Reynolds number with POD method［J］.Journal of Northwestern Polytechnical University,2014,32(4):612-617.(in Chinese)
[8]	刘浩,徐敏,叶茂.基于特征正交分解的跨声速流场重构和翼型反设计方法研究［J］.空气动力学学报,2012,30(4):539-545.LIU Hao,XU Min,YE Mao.Investigation of transonic flow field reconstruction and inverse airfoil design based on proper orthogonal decomposition ROM［J］.Acta Aerodynamica Sinica,2012,30(4):539-545.(in Chinese)
[9]	YAMADA K,FURUKAWA M,INOUE M,et al.Numerical analysis of tip leakage flow field in a transonic axial compressor rotor［C］∥Proceedings of the International Gas Turbine Congress.Tokyo:Academic Press,2003:1-8.
[10]	HAH C,HATHAWAY M,KATZ J.Investigation of unsteady flow field in a low-speed one and a half stage axial compressor:effects of tip gap size on the tip clearance flow structure at near stall operation［R］.ASME Paper 2014-GT-27094,2014.
[11]	HEWKIN-SMITH M,PULLAN G,GRIMSHAW S D,et al.The role of tip leakage flow in spike-type rotating stall inception［R］.ASME Paper 2017-GT-63655,2017.
[12]	张卓勋,吴艳辉,楚武利,等.激波/泄漏涡相互干扰对跨声压气机流动稳定性的影响［J］.航空动力学报,2010,25(7):1615-1621.ZHANG Zhuoxun,WU Yanhui,CHU Wuli,et al.Influence of shock/tip leakage vortex interaction on flow stability in a single-stage transonic axial compressor［J］.Journal of Aerospace Power,2010,25(7):1615-1621.(in Chinese)
[13]	石宝龙,岂兴明,矫津毅,等.二次流与叶顶间隙损失的数值研究［J］.航空动力学报,2009,24(5):1096-1100.SHI Baolong,QI Xingming,JIAO Jinyi,et al.Numerical analysis of the secondary flow and tip clearance leakage loss［J］.Journal of Aerospace Power,2009,24(5):1096-1100.(in Chinese)
[14]	SIROVICH L.Turbulence and the dynamics of coherent structures:Ⅰ coherent structures［J］.Quarterly of Applied Mathematics,1987,45(3):561-571.
[15]	MOORE R D,REID L.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78,respectively,and with design pressure ratio of 1.82［R］.NASA-TP-1974,E-259,1974.
[16]	VAN ZANTE D E,STRAZISAR A J,WOOD J R,et al.Recommendations for achieving accurate numerical simulation of tip clearance flows in transonic compressor rotors［J］.Journal of Turbomachinery,2000,122(4):733-742.