Mathematical model of a turboelectric propulsion system for aviation

In this study, the turboelectric propulsion system, one of the potential technologies proposed for modeling and simulation, was chosen. A high-fidelity mathematical model of GE T700 turboshaft engine created in MATLAB / Simulink was used as the main power source. The mathematical model of the selected gas turbine is combined with NASA electrical propulsion architectures designed for N-3X turboelectric aircraft. The scenario of working with a single engine is a critical design criterion in engine failures for twin-engine airplanes. Simulink mathematical model was used for the analysis of this scenario. Therefore, this study includes guidance on issues such as correct system design and equipment selection. Two important architectural approaches, Baseline Architecture and Inner Bus Tie Architecture, have been analyzed. Accordingly, the changes to be made based on the selected architecture and equipment differences are explained. In addition, some preliminary studies have been made on the most suitable power electronics applications for turboelectric architectures. The power requirements, distribution percentages, preliminary power rating and nominal power capacities of each electric unit of this turboelectric propulsion system are calculated using the GE T700 turboshaft engine model. This engine model is widely used today as the main power source. Turboshaft motor is connected to a 3-phase generator to convert the mechanical power into electrical power. A designed 6-pulse boost rectifier converts ac power to dc after the generator. Then the voltage level can be reduced based on the requirements of the motor with the assistance of a voltage source inverter. However, high voltage transfer reduces DC conduction losses. The mathematical modelling results of Baseline Architecture and Inner Bus Tie Architecture, which have different advantages compared to each other will guide new studies for various power applications. The power requirements, distribution percentages, preliminary power rating and nominal power capacities of each electric unit of the turboelectric propulsion system are calculated using the GE T700 turboshaft engine model, which is widely used today as the main power source. The turboshaft engine was connected to a 3-phase generator, providing energy conversion from mechanical to electrical. The electrical conversion will be rectified by a converter that increases the output of the three-phase generator and then reduced according to the requirements of the engine with the help of a voltage-source inverter. Transmitting the voltage at a higher level than required will reduce DC transmission losses. As a result of this study, the numerical results of the architectural studies have been observed and the infrastructure has been prepared for the studies to be carried out for different power systems.