Aerothermodynamics Analysis Of Axial Flow Aircraft Gas Turbine Engine Compressor

The axial flow type compressor is one of the most common compressor types in use today. Itrnfinds its major application in large aircraft gas turbine engine like those that power today’s jetrnaircraft.rnEarly axial flow aircraft engine compressors had pressure ratio of around 5:1 and require aboutrn10 stages. Over the years the overall pressure ratios available exceed 30: 1 due to continuedrnaerodynamic development that resulted in a steady increase in a stage pressure ratio with reducedrnnumber of stages. There has been in consequence a reduction in engine weight for a specificrnlevel of performance, which is particularly important for aircraft engines. These potential gainsrnhave now been fully realized as the result of intensive research into the Aero-thermodynamicsrnAnalysis of Axial Flow Aircraft Gas Turbine Engine Compressor. Therefore, careful design ofrncompressor blading based on aero-thermodynamic theory, experiment and computational fluidrndynamic (CFD) analysis is necessary not only to prevent useful losses but also to insure arnminimum of stalling troubles.rnThe complete analysis of this thesis is done to provide some part of design of an axialrncompressor suitable for a simple low-cost and low weight turbojet Aircraft Gas Turbine EnginernCompressor by using different research work on the aero-thermodynamic analysis of therncompressor.rnDetails of CFD analysis on the models of the compressor, using a commercial softwarern“FLUENT”, will be presented. The CFD simulation predictions were validated quantitativelyrnagainst the experimental data and the theoretical (calculated values) were then used to obtainrnfurther insights into the characteristics of the flow behaviors.rnTo calculate the work and power required by the compressor to sustain the flight, the blades ofrnthe compressor will be modeled, and the required equations will be developed. Finally a smallrnscale computer program will be developed to calculate the power (work) required by therncompressor and to determine other performance measuring parameters.

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