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<br /> <p align="justify">This tubular & reverse-flow annular combustion chambers are designed for gas turbine simulator system. Combustion chamber is positioned between compressor and turbine. Combustion chamber is designed to increase enthalpy without significant pressur...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/27189 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | <br />
<p align="justify">This tubular & reverse-flow annular combustion chambers are designed for gas turbine simulator system. Combustion chamber is positioned between compressor and turbine. Combustion chamber is designed to increase enthalpy without significant pressure loss. Existing combustion chamber is designed by conventional method of trial and error. To further increase its performance, an optimization is needed. The geometry of the combustion chamber is optimized to maximize efficiency, minimize pattern factor, minimize pressure loss and lower temperature on the combustion wall. Performance of the combustion chamber then evaluated by computational fluid dynamics simulation. Varying parameter is chosen based on sensitivity analysis with Spearman Correlation method to choose influential changes on geometry. After sampling process with Latin Hypercube Sampling (LHS) method and followed by interpolation with Kriging method, the combustion chamber then optimized using Multi Objective Genetic-Algorithm (MOGA). The final designs give better performance with a little increase in efficiency and good pattern factor. The effect of variation of FAR and off-design condition according to Performance Map Gas Turbine System will be analyzed on the optimum geometry that had produced by optimization process. <br />
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