Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations
This study concerns a 2.5 pressure ratio centrifugal compressor stage consisting of a splittered unshrouded impeller and a vaned diffuser. The aim of this paper is to investigate the modifications of the flow structure when the operating point moves from peak efficiency to near stall. The investigat...
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| Format: | Article |
| Language: | English |
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Wiley
2014-01-01
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| Series: | International Journal of Rotating Machinery |
| Online Access: | http://dx.doi.org/10.1155/2014/729629 |
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| _version_ | 1832551506720587776 |
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| author | Yannick Bousquet Xavier Carbonneau Guillaume Dufour Nicolas Binder Isabelle Trebinjac |
| author_facet | Yannick Bousquet Xavier Carbonneau Guillaume Dufour Nicolas Binder Isabelle Trebinjac |
| author_sort | Yannick Bousquet |
| collection | DOAJ |
| description | This study concerns a 2.5 pressure ratio centrifugal compressor stage consisting of a splittered unshrouded impeller and a vaned diffuser. The aim of this paper is to investigate the modifications of the flow structure when the operating point moves from peak efficiency to near stall. The investigations are based on the results of unsteady three-dimensional simulations, in a calculation domain comprising all the blade. A detailed analysis is given in the impeller inducer and in the vaned diffuser entry region through time-averaged and unsteady flow field. In the impeller inducer, this study demonstrates that the mass flow reduction from peak efficiency to near stall leads to intensification of the secondary flow effects. The low momentum fluid accumulated near the shroud interacts with the main flow through a shear layer zone. At near stall condition, the interface between the two flow structures becomes unstable leading to vortices development. In the diffuser entry region, by reducing the mass flow, the high incidence angle from the impeller exit induces a separation on the diffuser vane suction side. At near stall operating point, vorticity from the separation is shed into vortex cores which are periodically formed and convected downstream along the suction side. |
| format | Article |
| id | doaj-art-0227720d333c45dea3205ced9b3c1c60 |
| institution | Kabale University |
| issn | 1023-621X 1542-3034 |
| language | English |
| publishDate | 2014-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Rotating Machinery |
| spelling | doaj-art-0227720d333c45dea3205ced9b3c1c602025-02-03T06:01:11ZengWileyInternational Journal of Rotating Machinery1023-621X1542-30342014-01-01201410.1155/2014/729629729629Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus SimulationsYannick Bousquet0Xavier Carbonneau1Guillaume Dufour2Nicolas Binder3Isabelle Trebinjac4Liebherr-Aerospace Toulouse SAS, 408 avenue des Etats Unis, 31016 Toulouse, FranceDépartement d’Aérodynamique, Energétique et Propulsion, ISAE, Université de Toulouse, BP 54032, 31055 Toulouse Cedex 4, FranceDépartement d’Aérodynamique, Energétique et Propulsion, ISAE, Université de Toulouse, BP 54032, 31055 Toulouse Cedex 4, FranceDépartement d’Aérodynamique, Energétique et Propulsion, ISAE, Université de Toulouse, BP 54032, 31055 Toulouse Cedex 4, FranceLaboratoire de Mécanique des Fluides et d’Acoustique, Ecole Centrale de Lyon, UCB Lyon I, INSA, 36 avenue Guy de Collongue, 69134 Ecully Cedex, FranceThis study concerns a 2.5 pressure ratio centrifugal compressor stage consisting of a splittered unshrouded impeller and a vaned diffuser. The aim of this paper is to investigate the modifications of the flow structure when the operating point moves from peak efficiency to near stall. The investigations are based on the results of unsteady three-dimensional simulations, in a calculation domain comprising all the blade. A detailed analysis is given in the impeller inducer and in the vaned diffuser entry region through time-averaged and unsteady flow field. In the impeller inducer, this study demonstrates that the mass flow reduction from peak efficiency to near stall leads to intensification of the secondary flow effects. The low momentum fluid accumulated near the shroud interacts with the main flow through a shear layer zone. At near stall condition, the interface between the two flow structures becomes unstable leading to vortices development. In the diffuser entry region, by reducing the mass flow, the high incidence angle from the impeller exit induces a separation on the diffuser vane suction side. At near stall operating point, vorticity from the separation is shed into vortex cores which are periodically formed and convected downstream along the suction side.http://dx.doi.org/10.1155/2014/729629 |
| spellingShingle | Yannick Bousquet Xavier Carbonneau Guillaume Dufour Nicolas Binder Isabelle Trebinjac Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations International Journal of Rotating Machinery |
| title | Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations |
| title_full | Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations |
| title_fullStr | Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations |
| title_full_unstemmed | Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations |
| title_short | Analysis of the Unsteady Flow Field in a Centrifugal Compressor from Peak Efficiency to Near Stall with Full-Annulus Simulations |
| title_sort | analysis of the unsteady flow field in a centrifugal compressor from peak efficiency to near stall with full annulus simulations |
| url | http://dx.doi.org/10.1155/2014/729629 |
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