Abstract
To achieve the required performance goals and structural durability of gas turbine combustion systems, a design approach was formulated to guide the development effort of the combustor. The approach combines the capabilities of the analytical tools with well-established empirical correlations. By this means, the impact of systematic modification to the details of the burner is easily determined. The validation effort of the developed model included the utilization of the data obtained for a number of production combustors that significantly varied in design and concept. Fuels used in these combustors included typical aviation fuels such as JP-4 and DF-2 as well as specially prepared high-density fuels. Model validation also involved the application of the model in the development phases of an annular combustor. Several modifications to the dome and primary zone features were proposed in this effort. The predictions of the combustor performance and wall temperatures made using the present approach were found to be in good agreement with the measurements.
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