Thermodynamic optimization of ideal turbojet with afterburner engines using non-dominated sorting genetic algorithm II

Abstract In this study, the multi-objective optimization using genetic algorithm is carried out for optimization of the thermodynamic cycle of ideal turbojet with afterburner engines. The fast non-dominated sorting genetic algorithm II is used to obtain the solutions. The possible important conflicting thermodynamic objective functions that have been considered in this work are specific thrust, thrust-specific fuel consumption, propulsive efficiency (ηp), and thermal efficiency (ηt). Different pairs of these objective functions have been selected for two-objective optimization processes. These objectives have also been considered for a four-objective optimization problem using the multi-objective genetic algorithm of this work. The research demonstrates that the results of four-objective optimization can include those of two-objective optimization and, therefore, provide more choices for the optimal design of the thermodynamic cycle of ideal turbojet with afterburner engines.