Abstract
Optimization of inverted Brayton cycle engine is made by particle swarm optimization method in this study. The optimum specific thrust value is reached by staying within the optimization constraints. When the total temperature of the cooling section is examined, it is seen that a temperature above the freezing temperature of the air is obtained. A very high specific thrust value, 451 N.s/kg is obtained at the hypersonic flight Mach Number (5 Mach) as a result of optimization. Temperature decrease with increasing altitude effect performance dramatically as positive. Low preburner exit total temperature and turbine total pressure ratio values and high afterburner exit total temperature values are desirable in terms of performance but values of total temperature at cooling section effect performance conversely in terms of specific thrust and specific fuel consumption
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