Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.

Musa, Ahmad Shauqi (2009) Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa. Degree thesis, Universiti Teknologi MARA.


The gas turbine is a device that converts heat into work and also called as a combustion turbine which is a rotary engine. A simple gas turbine is based on the three main components: a compressor, a combustor and a turbine. This study covers on the gas turbine behavior and technology which are focuses on the effect of fan pressure ratio and altitude on overall performance of aero gas turbine. The whole idea of aero gas turbine such as turbofan and turbojet will be describe since the FPR value will be taken 1.3 up to 2.0 and the margin altitude value from 0 up to high altitude (11000km). Basically the manual analysis or calculation need more time and required high level understanding of gas turbine operation so we have developed a software by using MATLAB Simulink and graphical user interface (GUI) and the result will represent the prediction of gas turbine performance. The study method required and used to avoid the mistake occurs during the manual analysis and make a systematic data output accurately compare to manuals. The software of MATLAB simulink is represented in block diagram or model that will create a flow of aircraft gas turbine from the intake until the exhaust nozzle. Meanwhile, the significant of this study can make the student and society to get ease understanding the trend occurs for the selected margins. The main task of overall of the program is to gain the total thrust (FN) and specific fuel consumption (SFC) from the MATLAB simulink and GUI program. Then the study and analyzing is done on both final results in some conditions based on the correlation between fuel flow, thrust and SFC. The results for the fixed Mach number and altitude selected, an increasing of the pressure ratio (FPR) decreased the specific fuel consumption (SFC) and the small range given from specific thrust.


Item Type: Thesis (Degree)
Email / ID Num.
Musa, Ahmad Shauqi
Email / ID Num.
Thesis advisor
Mohd Noh, Mohd Hafiz
Subjects: T Technology > TJ Mechanical engineering and machinery > Heat engines
Divisions: Universiti Teknologi MARA, Shah Alam > Faculty of Mechanical Engineering
Keywords: Gas turbine, Aeroengine, Thermodynamic, combustion turbine
Date: 2009
Edit Item
Edit Item


[thumbnail of 31562.pdf] Text

Download (142kB)

Digital Copy

Digital (fulltext) is available at:

Physical Copy

Physical status and holdings:
Item Status:

ID Number




Statistic details