The main role of the auxiliary power unit in airplanes is to provide bleed air for the purposes of launching the main engines and to provide electricity when the main engines are not in operation. With the aim of defossilising the aviation sector, auxiliary power units are as well being developed in the way of using low-carbon fuels, which requires experimenting in a controlled laboratory environment and thus ensuring adequate power consumption. In the final thesis, a turboshaft engine GTCP85-98D is discused as it represents the auxiliary power unit of the airplane. It is capable of producing 120 V and 400 Hz of the electrical energy and also bleeds air. Based on the calculated energy balance of the engine, which is established due to the information available in the documentation and the analysis of the way how the auxiliary power unit works, the final thesis represents different topologies of the engine loading systems. The loading systems are estimated to be suitable for usage, research, and investment and introduction of possible support systems, as well. On the basis of the calculations, the most appropriate identified solution is the usage of a DC battery as it allows smaller connection capacities, while it is also sufficient for the auxiliary power unit to operate on its full power for several hours.
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