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Volume 30 Issue 06
Jun.  2004
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Journal of Beijing University of Aeronautics and Astronautics  > 2004  >  30(06): 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(06): 577-582. (in Chinese)
Citation: 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(06): 577-582. (in Chinese)
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Staggered finite volume method for turbomachinery viscous flow field numerical investigation

  • School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 30 Jun 2003
  • Publish Date: 30 Jun 2004
    Abstract
  • A compact staggered mesh limited control volume scheme was used in a three dimensional steady computational fluid dynamics (CFD) code to solve the favre-averaged Navier-Stokes equations and k-ε turbulence model equations more tightly, after Fourier analysis for odd-even decoupled mode in several staggered mesh discretizations. NASA Rotor 67 flow field was calculated and flow structures in terms of relative mach numbers were presented. The excellent agreement between simulations and experiments not only under design condition, but also un-design condition demonstrates the code's predictive capability. The cause of the discrepancies was also discussed. Meanwhile the code has the advantage of calculation efficiency compared with some other software.

     

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  • [1] Liu F, Zheng X. A strongly coupled time-marching method for solving the navier-stokes and k-ε turbulence model equation with multigrid. Journal of Computational Physics, 1996, 128:289~300 [2]Turner M G, Jennions I K. An investigation of turbulence modeling in transonic fans including a novel implementation of an implicit k-ε turbulence Model. ASME 92-GT-308 [3]Jameson A. Numerical solutin of the euler equations by finite volume methods using runge kutta time stepping schemes. AIAA-81-1259 [4] Fottner L. Test cases for computation of internal flows in aero engine components. AGARD-AR-275, Neubigerg Germany, 1990 [5] 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,Gui Xingmin.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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