Abstract
The aim of this study is to optimize the performance functions of turbofan engines. In this way, the multi-objective genetic algorithm is employed to optimal design of turbofan with considering the offdesign model of engine. The design variables are high-pressure compressor pressure ratio, lowpressure compressor pressure ratio, fan pressure ratio and bypass ratio. They are calculated in such a way that the performance functions are at their best conditions simultaneously. The performance functions are specific thrust at take-off, and thrust specific fuel consumption, propulsive, thermal, and overall efficiencies at cruise. The optimization is carried out using the modified NSGA II which is among the best multi-objective genetic algorithm methods. The results of this optimization will be a set of vectors which the designer may choose one of those according to the problem conditions.
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