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Development of a 250 kW Electric Power Generation System for a More Electric Aircraft


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DOI: https://doi.org/10.15866/iree.v16i4.19410

Abstract


This paper describes the design process of a 250 kW power generation system with high energy density for use in a more electric aircraft. This task is considered in terms of developing a starter-generator, a transformer-rectifier unit, as well as selecting voltage in order to minimize the cables mass passing on board the aircraft. The analysis of the efficiency of the structures of power generation systems on board the aircraft has been carried out. Their advantages and disadvantages are considered. With the help of analytical methods and computer modeling methods, three different topologies of starter-generators have been calculated, and the most suitable option in terms of weight and dimensions has been selected. In addition, a market analysis has been made and it has showed that there is a very limited amount of mass-produced transformer-rectifier units with the required voltage. Therefore, it has been decided to design a transformer-rectifier unit for this voltage class. In order to verify the calculations, experimental studies of the starter-generator, as the main element of the studied system in various operating modes, have been carried out. Experimental studies have been carried out in idle mode, under load at constant and variable speed, temperature measurements have been taken. The results of the experimental studies have confirmed the correctness of the calculation methods. The paper may be of interest to researchers and engineers involved in the creation of aviation power supply systems, aircraft electrical machines, and technologies for a more electric and fully electric aircraft.
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Keywords


Starter/Generator; Transformer-Rectifier Unit; Power Generation System; More Electric Aircraft

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