Abstract
Catalytically supported thermal combustion has been successfully incorporated into a low-pressure-r atio gas turbine type system. Excellent emissions performance was obtained utilizing gaseous propane fuel. A combustor design concept has been developed that is applicable to gaseous fueled gas turbine engines. A working solution to the important questions related to the use of this type of combustor in a dynamic turbine environment has been demonstrated for low-pressure-ratio simple-cycle engines. Both straight-through flow and reverse-flow combustors have been developed for use in conjunction with the catalyst system. Fuel turndown ranges approximating 10:1 have been achieved in both systems tested, the range being limited in this instance by the machine airflow capacity. For systems of the type discussed herein, increases in combustor diameters no greater than 50% with respect to conventional combustors would be required for low-pressure-ratio engine applications. A prime goal for high-pressure-ratio applications is the development of short residence time mixing configurations.
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