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System analysis of turbo-electric and hybrid-electric propulsion systems on a regional aircraft

Part of: 31st Congress of The International Council of the Aeronautical Sciences (ICAS)

Published online by Cambridge University Press:  01 August 2019

Hendrik Gesell ,
Florian Wolters Open the ORCID record for Florian Wolters [Opens in a new window]  and
Martin Plohr
Hendrik Gesell
Affiliation:
German Aerospace Center (DLR)Institute of Propulsion Technology Linder Hoehe, 51147 Cologne, Germany
Florian Wolters*
Affiliation:
German Aerospace Center (DLR)Institute of Propulsion Technology Linder Hoehe, 51147 Cologne, Germany
Martin Plohr
Affiliation:
German Aerospace Center (DLR)Institute of Propulsion Technology Linder Hoehe, 51147 Cologne, Germany
*
Florian.Wolters@dlr.de
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Abstract

The increasing environmental requirements in the air transport sector pose great challenges to the aviation industry and are key drivers for innovation. Besides various approaches for increasing the efficiency of conventional gas turbine engines, electric propulsion systems have moved into the focus of aviation research. The first electric concepts are already in service in general aviation. This study analyses the potentials of electric and turbo hybrid propulsion systems for commercial aviation. Its purpose is to compare various architectures of electrical powertrains with a conventional turboprop on a regional aircraft, similar to the ATR 72, on engine and flight mission levels. The considered architectures include a turbo-electric (power controlled and direct driven), hybrid-electric (serial and parallel) and a pure electric concept. Their system weights are determined using today’s technology assumptions. With the help of performance models and flight mission calculations the impact on fuel consumption, CO ${}_{2}$ emissions and aircraft performance is evaluated.

Keywords

Aircraft engineGas turbine performanceTurbo-electricHybrid-electric
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1268 , October 2019 , pp. 1602 - 1617
Copyright
© Royal Aeronautical Society 2019 

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