Losses and blade tip clearance for a centrifugal compressor
The present paper presents the numerical analysis for a transonic centrifugal compressor using steady state CFD. The blade tip clearance effect over the position of shock waves, tip losses and the performances of the impeller are studied. Numerical simulations have been performed using RANS modellin...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
National Institute for Aerospace Research “Elie Carafoli” - INCAS
2018-06-01
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| Series: | INCAS Bulletin |
| Subjects: | |
| Online Access: | http://bulletin.incas.ro/files/dumitrescu_stanciuc_gherman_dragan_vol_10_iss_2.pdf |
| Summary: | The present paper presents the numerical analysis for a transonic centrifugal compressor using steady state CFD. The blade tip clearance effect over the position of shock waves, tip losses and the performances of the impeller are studied. Numerical simulations have been performed using RANS modelling, with the k-omega SST turbulence model (Shear Stress Transport). Eight cases were taken into consideration for the impeller with the following blade tip clearances values: 0 mm, 0.1 mm, 0.3 mm, 0.4 mm, 0.5mm, 0.7 mm, 1 mm, 2 mm, at the same operating conditions. For the entire stage only seven cases were studied, without the value for 0.1 mm because of its abnormal behaviour, as can be seen in the case of the impeller simulations. Results showed that the position of the shock wave does not change with the increase of the tip clearance. Aerodynamic losses due to shock wave, secondary flow and turbulence can be seen in the polytropic efficiency of the centrifugal impeller and the difference between the two extreme cases is about 3.2 %. |
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| ISSN: | 2066-8201 2247-4528 |