The initial flight test evaluation phase of the performance seeking control (PSC) algorithm has been completed for one engine, subsonic, part power, and military power operation on an F-15 aircraft, using a PW1128 engine. The algorithm is designed to optimize the quasi-steady-state performance of an engine for three primary modes of operation: the minimum fuel, the minimum fan turbine inlet temperature (FTIT), and the maximum thrust modes. The minimum fuel mode is designed to minimize thrust-specific fuel consumption during cruise conditions. The minimum FTIT mode is designed to extend the turbine life by decreasing the F7'I7' during cruise and accelerating flight conditions. The maximum thrust mode is designed to maximize net propulsive force at military power. Decreases in thrust-specific fuel consumption of approximately 1 percent have been measured in the minimum fuel mode; integrated over the life of the aircraft and fleet size, these fuel savings are significant. Decreases of up to approximately 100°R in FTIT were measured in the minimum FTIT mode. Temperature reductions of this magnitude are significant and would more than double engine life ifFTIT were the only factor. Thrust increases of up to approximately 12 percent were measured in the maximum thrust mode. The system dynamics of the closed-loop algorithm operation appear good. The preliminary flight phase has provided a general validation of the *Aerospace Engineer. Member AIAA.
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