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

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 focus...

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Main Author:	Musa, Ahmad Shauqi
Format:	Thesis
Language:	English
Published:	2009
Subjects:	Heat engines
Online Access:	https://ir.uitm.edu.my/id/eprint/31562/1/31562.pdf
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id	my-uitm-ir.31562
record_format	uketd_dc
spelling	my-uitm-ir.315622020-07-02T01:50:37Z Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa. 2009 Musa, Ahmad Shauqi Heat engines 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. 2009 Thesis https://ir.uitm.edu.my/id/eprint/31562/ https://ir.uitm.edu.my/id/eprint/31562/1/31562.pdf text en public degree Universiti Teknologi MARA Faculty of Mechanical Engineering Mohd Noh, Mohd Hafiz
institution	Universiti Teknologi MARA
collection	UiTM Institutional Repository
language	English
advisor	Mohd Noh, Mohd Hafiz
topic	Heat engines
spellingShingle	Heat engines Musa, Ahmad Shauqi Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
description	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.
format	Thesis
qualification_level	Bachelor degree
author	Musa, Ahmad Shauqi
author_facet	Musa, Ahmad Shauqi
author_sort	Musa, Ahmad Shauqi
title	Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
title_short	Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
title_full	Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
title_fullStr	Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
title_full_unstemmed	Prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / Ahmad Shauqi Musa.
title_sort	prediction of an aeroengine performance analysis and thermodynamic parametric study (fan pressure ratio) / ahmad shauqi musa.
granting_institution	Universiti Teknologi MARA
granting_department	Faculty of Mechanical Engineering
publishDate	2009
url	https://ir.uitm.edu.my/id/eprint/31562/1/31562.pdf
_version_	1783734129247911936

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

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