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Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack

Intake of a supersonic gas turbine requires the highest possible total pressure recovery and minimal total pressure lost in order to obtain an efficient operation. The supersonic intake is mainly affected by two substantial factors which are the angle of attack and the geometry of the spike (wedge a...

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Main Author: Tan, Kien Weng
Format: Final Year Project
Published: Universiti Teknologi Petronas 2009
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://utpedia.utp.edu.my/662/
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spelling my-utp-utpedia.6622017-01-19T15:49:04Z http://utpedia.utp.edu.my/662/ Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack Tan, Kien Weng TJ Mechanical engineering and machinery Intake of a supersonic gas turbine requires the highest possible total pressure recovery and minimal total pressure lost in order to obtain an efficient operation. The supersonic intake is mainly affected by two substantial factors which are the angle of attack and the geometry of the spike (wedge angle). At zero angle of attack, the solution is quite direct, but at non-zero angle of attack, the shock system structure will be affected and the flow distribution will be unsymmetrical in the upper (leeside) and the lower side (windward side) of the inlet. The objective of this work is to analyze the thermo fluid mechanism and to investigate the flow characteristic in the diffuser part of the intake. The analysis is carried out under the assumption of viscous, steady, 2D compressible fluid flow. The external part (shock system part) is to be modelled and analyzed analytically. The shock system part is successfully modelled using Microsoft Excel. The internal part (diffuser) will be simulated and analyzed numerically using CFD software. The available FLUENT and GAMBIT software in the department will be used for modelling and simulation. In conclusion, the study on combination effect of angle of attack and wedge angle is very essential as it directly affect the performance of the compressor and in turn, the gas turbine operation Universiti Teknologi Petronas 2009 Final Year Project NonPeerReviewed Tan, Kien Weng (2009) Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack. Universiti Teknologi Petronas, Sri Iskandar,Tronoh,Perak. (Unpublished)
institution Universiti Teknologi Petronas
building UTP Resource Centre
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Petronas
content_source UTP Electronic and Digitized Intellectual Asset
url_provider http://utpedia.utp.edu.my/
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
Tan, Kien Weng
Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
description Intake of a supersonic gas turbine requires the highest possible total pressure recovery and minimal total pressure lost in order to obtain an efficient operation. The supersonic intake is mainly affected by two substantial factors which are the angle of attack and the geometry of the spike (wedge angle). At zero angle of attack, the solution is quite direct, but at non-zero angle of attack, the shock system structure will be affected and the flow distribution will be unsymmetrical in the upper (leeside) and the lower side (windward side) of the inlet. The objective of this work is to analyze the thermo fluid mechanism and to investigate the flow characteristic in the diffuser part of the intake. The analysis is carried out under the assumption of viscous, steady, 2D compressible fluid flow. The external part (shock system part) is to be modelled and analyzed analytically. The shock system part is successfully modelled using Microsoft Excel. The internal part (diffuser) will be simulated and analyzed numerically using CFD software. The available FLUENT and GAMBIT software in the department will be used for modelling and simulation. In conclusion, the study on combination effect of angle of attack and wedge angle is very essential as it directly affect the performance of the compressor and in turn, the gas turbine operation
format Final Year Project
author Tan, Kien Weng
author_facet Tan, Kien Weng
author_sort Tan, Kien Weng
title Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
title_short Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
title_full Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
title_fullStr Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
title_full_unstemmed Simulation And Flow Characterization Of Spiked Supersonic Gas Turbine Intake At Non-Zero Angle Of Attack
title_sort simulation and flow characterization of spiked supersonic gas turbine intake at non-zero angle of attack
publisher Universiti Teknologi Petronas
publishDate 2009
url http://utpedia.utp.edu.my/662/
_version_ 1739830686780489728
score 13.211869

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