Viscous Analysis of Three-Dimensional Rotor Flow Using a Multigrid MethodSource: Journal of Turbomachinery:;1994:;volume( 116 ):;issue: 003::page 435Author:A. Arnone
DOI: 10.1115/1.2929430Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: A three-dimensional code for rotating blade-row flow analysis has been developed. The space discretization uses a cell-centered scheme with eigenvalue scaling for the artificial dissipation. The computational efficiency of a four-stage Runge–Kutta scheme is enhanced by using variable coefficients, implicit residual smoothing, and a full-multigrid method. An application is presented for the NASA rotor 67 transonic fan. Due to the blade stagger and twist, a zonal, nonperiodic H-type grid is used to minimize the mesh skewness. The calculation is validated by comparing it with experiments in the range from the maximum flow rate to a near-stall condition. A detailed study of the flow structure near peak efficiency and near stall is presented by means of pressure distribution and particle traces inside boundary layers.
keyword(s): Flow (Dynamics) , Rotors , Blades , Eigenvalues , Pressure , Particulate matter , Energy dissipation AND Boundary layers ,
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| contributor author | A. Arnone | |
| date accessioned | 2017-05-08T23:45:49Z | |
| date available | 2017-05-08T23:45:49Z | |
| date copyright | July, 1994 | |
| date issued | 1994 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28637#435_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/114546 | |
| description abstract | A three-dimensional code for rotating blade-row flow analysis has been developed. The space discretization uses a cell-centered scheme with eigenvalue scaling for the artificial dissipation. The computational efficiency of a four-stage Runge–Kutta scheme is enhanced by using variable coefficients, implicit residual smoothing, and a full-multigrid method. An application is presented for the NASA rotor 67 transonic fan. Due to the blade stagger and twist, a zonal, nonperiodic H-type grid is used to minimize the mesh skewness. The calculation is validated by comparing it with experiments in the range from the maximum flow rate to a near-stall condition. A detailed study of the flow structure near peak efficiency and near stall is presented by means of pressure distribution and particle traces inside boundary layers. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Viscous Analysis of Three-Dimensional Rotor Flow Using a Multigrid Method | |
| type | Journal Paper | |
| journal volume | 116 | |
| journal issue | 3 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.2929430 | |
| journal fristpage | 435 | |
| journal lastpage | 445 | |
| identifier eissn | 1528-8900 | |
| keywords | Flow (Dynamics) | |
| keywords | Rotors | |
| keywords | Blades | |
| keywords | Eigenvalues | |
| keywords | Pressure | |
| keywords | Particulate matter | |
| keywords | Energy dissipation AND Boundary layers | |
| tree | Journal of Turbomachinery:;1994:;volume( 116 ):;issue: 003 | |
| contenttype | Fulltext |