The Ultra Compact Combustor (UCC) promises to greatly reduce the size of a gas turbine engines combustor by burning fuel circumferentially. This design employs a combustor center body that changes the flow path angle. The first goal of the present investigation was to experimentally evaluate five cooling configurations to quantify the impact of internal geometry and film-cooling on the body's surface temperature distribution. The second goal of this investigation was to understand the complex airflow and combustion dynamics that resulted in the hottest combustor exit temperatures. Prior studies have determined what UCC operating conditions created the highest exit temperatures, but not why.
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