Abstract
This paper presents a conceptual study of a regional aircraft with a turboelectric propulsion system and boundary layer ingestion. The concept was designed by the installation of an additional electric propulsor at the aircraft tail cone, which is driven by generators installed on both underwing engines, aiming to ingest the fuselage boundary layer and improve the aircraft overall performance. The proposed configuration can be considered an aircraft reengining, targeting minimal changes on the reference aircraft platform, the Embraer 175-E1. Parametric variations of the thrust split ratio as well as the electric fan pressure ratio were done in order to create a design space of possible solutions for the proposed concept and also to provide insights of the aircraft key variables trends. From that, an optimized configuration not only in terms of efficiency but also regarding the concept feasibility was chosen and compared to the reference aircraft. It was determined that the studied propulsion system has a potential to provide specific air range benefits in the order of 4% to 7%.
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