Design of the “integrated into an aircraft engine starter-generator – dual-flow turbojet engine” system as a part of the electrified aircraft engine concept creation

Abstract

In this paper, the authors considered the "integrated into the aircraft engine starter-generator – dual-flow turbojet engine" system design within the electrified aircraft engine creation framework. Information about electrified aircraft engine is given and an analysis of the electric machines’ types, which are suitable for the implementation in the electrified aircraft engine, is carried out. Possible options for starter-generator integration into the dual-flow turbojet engine are considered and their key features are analyzed. The starter-generator into the starter-generator integration general features are revealed, which must be considered in the "integrated into the aircraft engine starter-generator – dual-flow turbojet engine" system design. An original multidisciplinary "integrated into the aircraft engine starter-generator – dual-flow turbojet engine" system design algorithm has been proposed. 400 kW integrated into the aircraft engine starter-generator part, located on the dual-flow turbojet engine low-pressure shaft, calculations were carried out.