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�������պ����ѧѧ�� 2005, Vol. 31 Issue (05) :529-534    DOI:
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Numercial simulation of transonic axial compressor rotor flow with tip clearance using multi-block meshes
Li Minjiang, Gui Xingmin*
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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Abstract�� To investigate the tip clearance flow in transonic compressor rotor, a 3D numerical simulation code was developed. The 3D flow fields of a transonic axial compressor, NASA Rotor 37, with considering the tip clearance were simulated using Reynolds-averaged Navier-Stokes equations with high Reynolds-Number ��k-� turbulence model and wall function. A multi-block grid was used for the tip clearance domain of the rotor, which couples with the main flow without any tip clearance experiential models, as well as avoids reducing the tip clearance scale under the assumption of Vena convergence effects. The Navier-Stokes equations and turbulence equations were strongly coupled by staggered finite volume scheme in order to get more precise results. The 3D simulation results were compared with the experimental data. The mid-span flow structures are consistent with experimental result, as well as the slight different details exist in the tip and hub flow structures because of the eddy viscosity model and shock-wave.
Keywords�� grids   numerical computation   \%k-ε\% turbulence model   staggered mesh scheme     
Received 2003-12-03;


About author: ������(1976-),��,������,��ʿ��, Liminjiang@163.com.
������, ������.�������������ѹ������Ҷ���϶����[J]  �������պ����ѧѧ��, 2005,V31(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 A, 2005,V31(05): 529-534
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