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Abstract
This thesis presents a numerical computation performed to investigate the convective heat transfer characteristics of a gas turbine can combustor under non - reacting flow conditions in a reynolds number range between 50,000 and 600,000 with a characteristic swirl number of 0.7. in this thesis, a CFD package was used to predict the heat transfer and flow characteristics in combustion chamber. It is observed that the flow filed in the combustor is characterized by an expanding swirling flow, which impinges on the liner wall close to the inlet of the combustor. The impinging shear layer is responsible for the peak location of heat transfer augmentation