Aerothermodynamics Analysis of Axial Flow Aircraft Gas Turbine Engine Compressor
| dc.contributor.advisor | Tesfaye, Dama (PhD) | |
| dc.contributor.author | Tilahun, Nigussie | |
| dc.date.accessioned | 2021-04-01T08:56:13Z | |
| dc.date.accessioned | 2023-11-18T06:32:22Z | |
| dc.date.available | 2021-04-01T08:56:13Z | |
| dc.date.available | 2023-11-18T06:32:22Z | |
| dc.date.issued | 2009-10-05 | |
| dc.description.abstract | The axial flow type compressor is one of the most common compressor types in use today. It finds its major application in large aircraft gas turbine engine like those that power today’s jet aircraft. Early axial flow aircraft engine compressors had pressure ratio of around 5:1 and require about 10 stages. Over the years the overall pressure ratios available exceed 30: 1 due to continued aerodynamic development that resulted in a steady increase in a stage pressure ratio with reduced number of stages. There has been in consequence a reduction in engine weight for a specific level of performance, which is particularly important for aircraft engines. These potential gains have now been fully realized as the result of intensive research into the Aero-thermodynamics Analysis of Axial Flow Aircraft Gas Turbine Engine Compressor. Therefore, careful design of compressor blading based on aero-thermodynamic theory, experiment and computational fluid dynamic (CFD) analysis is necessary not only to prevent useful losses but also to insure a minimum of stalling troubles. The complete analysis of this thesis is done to provide some part of design of an axial compressor suitable for a simple low-cost and low weight turbojet Aircraft Gas Turbine Engine Compressor by using different research work on the aero-thermodynamic analysis of the compressor. Details of CFD analysis on the models of the compressor, using a commercial software “FLUENT”, will be presented. The CFD simulation predictions were validated quantitatively against the experimental data and the theoretical (calculated values) were then used to obtain further insights into the characteristics of the flow behaviors. To calculate the work and power required by the compressor to sustain the flight, the blades of the compressor will be modeled, and the required equations will be developed. Finally a small scale computer program will be developed to calculate the power (work) required by the compressor and to determine other performance measuring parameters. | en_US |
| dc.identifier.uri | http://etd.aau.edu.et/handle/12345678/25894 | |
| dc.language.iso | en_US | en_US |
| dc.publisher | Addis Ababa University | en_US |
| dc.subject | Axial Flow | en_US |
| dc.subject | Aerothermodynamics | en_US |
| dc.subject | Aircraft | en_US |
| dc.subject | Turbine Engine Compressor | en_US |
| dc.title | Aerothermodynamics Analysis of Axial Flow Aircraft Gas Turbine Engine Compressor | en_US |
| dc.type | Thesis | en_US |