Modeling and Performance Optimization of Turboelectric Propulsion System

Focusing on the performance of the turboelectric propulsion system, characteristic component models such as the motor and ducted fan were developed based on a component-level modeling approach. These models were then integrated with the conventional component models of a separate-exhaust turbofan engine to establish a steady-state performance calculation model for a “separate-exhaust turbofan engine + ducted fan” configuration, with a certain degree of general applicability. Based on this model, the influence of design parameters on the overall system performance was first investigated, and the optimal ranges of the design parameters were determined. Then, with the objective of minimizing the specific fuel consumption (SFC) at the design point, design-point optimization and steady-state performance calculations were carried out. Finally, the optimized turboelectric propulsion system was compared with a high bypass ratio turbofan engine having the same cycle parameters. The results show that, at the design point, the net thrust of the turboelectric propulsion system increases by 4.12% compared with the baseline condition, while the SFC decreases by 10.62%. Compared to a high bypass ratio turbofan engine with the same performance level, the bypass ratio of the main engine in the turboelectric propulsion system is reduced by 50%, and the inlet physical airflow is reduced by 52.5%.