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

• Main Author: Musa, Ahmad Shauqi
• Format: Thesis
• Language: English
• Published: 2009
• Subjects: Heat engines
• Online Access: http://ir.uitm.edu.my/id/eprint/31562/1/31562.pdf; http://ir.uitm.edu.my/id/eprint/31562/

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.