Aerothermodynamics Analysis of Axial Flow Aircraft Gas Turbine Engine Compressor
No Thumbnail Available
Date
2009-10-05
Authors
Journal Title
Journal ISSN
Volume Title
Publisher
Addis Ababa University
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.
Description
Keywords
Axial Flow, Aerothermodynamics, Aircraft, Turbine Engine Compressor