مشروع البحث: CFD modelling of the bore flow in the compressor stages of a gas turbine engine
| dc.contributor.advisor | Dr. Michael Wilson | |
| dc.date.accessioned | 2026-01-06T10:22:50Z | |
| dc.date.available | 2026-01-06T10:22:50Z | |
| dc.description | The most significant observation made when changing the Rossby number to a lower value was the suppression of the vortices causing dips observed in the swirl number at the high Rossby number case. Blocking the first cavity in the rig was discovered to have significant impact on the flow. However, the a more streamlines inlet boundary resulted in better velocity measurement. Furthermore, the velocity measurements seemed qualitatively accurate, however, due to discrepancies in the boundary conditions used and the 2D model are likely to give unrealistic results. | |
| dc.description.abstract | In order to determine the radial growth needed to estimate the allowable clearance between blades and casing, many parameters must be investigated to get an accurate representation of the flow in the bore of a compressor. A total of seven CFD cases investigating the flow in isothermal rotating cavities were analysed. The effect of varying the Rossby number by varying the axial and rotational Reynolds numbers on the flow in the rotating cavities is explored. | |
| dc.identifier | 897 | |
| dc.identifier.uri | https://dspace.academy.edu.ly/handle/123456789/1882 | |
| dc.subject | gas turbine engine | |
| dc.title | CFD modelling of the bore flow in the compressor stages of a gas turbine engine | |
| dspace.entity.type | Project | |
| project.endDate | 2018 | |
| project.funder.name | هندسة طيران | |
| project.investigator | المهدي عادل محمد المسلاتي | |
| project.startDate | 2017 |