Please use this identifier to cite or link to this item:
|Title:||Diffuser performance of centrifugal compressor in supercritical CO <inf>2</inf> power systems|
|Keywords:||upercritical CO2;turbomachinary desing;computational fluid dynamics;real gas aerothermodynamics|
|Citation:||Energy Procedia, 2019, 161 pp. 438 - 445|
|Abstract:||This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) The paper focuses on understanding the performance of a vaned diffuser in a supercritical CO 2 compressor using real gas assumptions. The rapidly changing properties of CO 2 in the non-ideal thermodynamic region can have a significant impact on the performance of the diffuser. To account for this, the relationship between the flow properties (i.e. fundamental derivative) and the local geometry (i.e. cross-sectional area of the nozzle) has been discussed theoretically. To examine it analytically, the study has considered the influence of real gas properties on the performance of a vaned diffuser using computational fluid dynamics (CFD) modelling. The selected compressor stage geometry is similar to the compressor impeller tested in the Sandia sCO 2 compression loop facility. The effect of changes in the number of blades and the corresponding changes in the cross throat area on the flow properties such as density and speed of sound were investigated and discussed. The results illustrate that a diffuser with a higher number of blades (smaller throat area) compared to a diffuser with a wider throat area has a higher probability of creating flow instability in the passage stage.|
|Appears in Collections:||Dept of Mechanical Aerospace and Civil Engineering Research Papers|
Items in BURA are protected by copyright, with all rights reserved, unless otherwise indicated.