Performance optimization of flight profile defined variable cycle propulsion system

Within the scope of this thesis; on-design and off-design thrust models are developed by obtaining the performance and energy equations for the flight phases of the variable cycle turbofan engine model (VCE). On the other hand, with the Genetic Algorithm approach, the optimization of several parameters such as total efficiency, specific thrust and specific fuel consumption of VCE is carried out with a specific code that is developed for this study. For the VCE model obtained in the thesis, a flight mission is determined and flight performance parameters (such as lift, drag etc.) are calculated for each flight phase. In addition, specific entropy values for the input-output points of each component and entropy generation of the main components of the VCE are calculated. Furthermore, an algorithm that calculates the exergetic parameters of the VCE model and its components is developed. Based on this analysis, exergoeconomic analysis of the VCE is performed. Exergy and exergoeconomic parameters of VCE for on-design, off-design and determined flight mission phases are computed with the developed exergetic and exergoeconomic algorithms. Finally, at off-design (for düz uçuş flight), performance and exergetic parameters regarding the VCE model are modeled in different flight conditions. The results of analysis obtained for the VCE are compared with the similar engine model used in fighter aircraft in terms of performance and sustainability. Keywords: Variable cycle turbofan, Gas turbines, Exergy, Propulsion, Optimization, Flight mechanics