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多块网格计算跨音压气机带叶尖间隙流场

李泯江 桂幸民

李泯江, 桂幸民. 多块网格计算跨音压气机带叶尖间隙流场[J]. 北京航空航天大学学报, 2005, 31(05): 529-534.
引用本文: 李泯江, 桂幸民. 多块网格计算跨音压气机带叶尖间隙流场[J]. 北京航空航天大学学报, 2005, 31(05): 529-534.
Li Minjiang, Gui Xingmin. Numercial simulation of transonic axial compressor rotor flow with tip clearance using multi-block meshes[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(05): 529-534. (in Chinese)
Citation: Li Minjiang, Gui Xingmin. Numercial simulation of transonic axial compressor rotor flow with tip clearance using multi-block meshes[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(05): 529-534. (in Chinese)

多块网格计算跨音压气机带叶尖间隙流场

基金项目: 国家自然科学基金资助项目(50076001,50136010)
详细信息
    作者简介:

    李泯江(1976-),男,重庆人,博士后, Liminjiang@163.com.

  • 中图分类号: O 357; V 211

Numercial simulation of transonic axial compressor rotor flow with tip clearance using multi-block meshes

  • 摘要: 开发了三维数值模拟程序研究轴流跨音转子叶尖间隙流动,应用高雷诺数k-ε湍流模型加壁面函数的方法,计算了轴流跨音转子NASA Rotor37在设计转速下的流场.叶尖间隙采用分区的H型网格和主流区连续对接耦合计算,没有用间隙模型,也没有考虑Vena收缩效应而减小间隙量.在用有限体积法对Navier-Stokes方程和湍流方程进行空间离散的过程中采用了交错网格的方法将N-S方程与湍流方程紧密地耦合在一起,从而提高了计算精度.计算结果和实验数据进行了详细的比较和分析.结果表明,中部叶展具有与实验结果非常一致的流场特征,根、尖区流场则因涡粘假设和激波问题的存在而使流动细节与实验结果略有偏差.

     

  • [1] Suder K L, Celestina M L. Experimental and computational investigation of the tip clearance in a transonic axial compressor rotor. ASME 94-GT-365, American:American Society of Mechanical Engineers,1994 [2] Chima R V. Calculation of tip clearance effects in a transonic rotor. ASME 96-GT-114, American:American Society of Mechanical Engineers,1996 [3] Arima T, Sonoda T, Shirotori M, et al. A numerical investigation of transonic axial compressor rotor flow using a low-reynolds-number k-ε turbulence model. ASME 97-GT-82, American:American Society of Mechanical Engineers, 1997 [4] 宁方飞. 考虑真实几何复杂性的跨音压气机内部流动的数值模拟. 北京:北京航空航天大学动力系,2002 Ning Fangfei. Numerical investigation of flows in transonic compressor with real geometrical complexities. Beijing:Dept of Propulsion, Beijing University of Aeronautics and Astronautics, 2002(in Chinese) [5] Jameson A. Numerical solutin of the Euler equations by finite volume methods using Runge Kutta time stepping schemes. AIAA 81-1259, American:American Institute of Aeronautics and Astronantics, 1981 [6] Liu Feng, Zheng Xiaoqing. Staggered finite volume scheme for solve cascade flow with a k-ω turbulence model [J]. AIAA Journal, 1994,32(8):1589~1597 [7] Mark G T, Ian K J. An investigation of turbulence modeling in transonic fans including a novel implementation of an implicit k-ε turbulence model. ASME 92-GT-308, American:American Society of Medanical Engineers,1992 [8] 李泯江,桂幸民. 用于叶轮机械流场计算的交错网格有限体积法 [J]. 北京航空航天大学学报,2004,30(6):577~582 Li Minjiang, Gui Xingmin. Staggered finite volume method for turbomachinery viscous flow field numerical investigation[J]. Journal of Beijing University of Aeronautics and Astronautics,2004,30(6):577~582(in Chinese) [9] Strzisar A J, Wood J R, Hathaway M D, et al. Laser anmometer measurement in a transonic axial-flow fan rotor. NASA-TP-2879, American:National Aeronantics and Space Administration,1989 [10] 敬荣强,李泯江,桂幸民. 高负荷跨音压气机叶尖间隙流动的数值分析与比较[J]. 航空动力学报,2003,18(6):827~831 Jing Rongqiang, Li Minjiang, Guixingmin. Numerical analysis and comparison on the tip-clearance flow of a high-loading transonic compressor[J]. Journal of Aerospace power,2003,18(6):827~831(in Chinese)
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出版历程
  • 收稿日期:  2003-12-03
  • 网络出版日期:  2005-05-31

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