Finding the Operating Limits and Optimal Configuration of an Electrically Assisted Turbofan

Master thesis (2019)

Authors

M.R. van Holsteijn Aerospace Engineering

Contributors

A. Gangoli Rao Flight Performance and Propulsion - Aerospace Engineering (mentor)
F. Yin Flight Performance and Propulsion - Aerospace Engineering (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2019 Merijn van Holsteijn
More Info
expand_more

Published Date

19-09-2019

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Abstract

Hybrid electric propulsion is a promising new technology to reduce emissions and fuel consumption of an aircraft. In this study a parallel hybrid electric configuration is considered. Since electric motors supply power in the most demanding take-off and climb phases to achieve the required thrust, the turbofan can be redesigned.

It was found that the cruise thrust specific fuel consumption could be improved, even though no electric power is supplied in that phase. The hybrid-electric aircraft shows potential to save fuel over a complete mission. Most of these savings are however achieved due to fully electric taxiing. The weight of the electrical system largely offsets the efficiency improvements of the gas turbine during flight. Given that optimistic technology levels are used for these results, parallel hybrid electric propulsion is not expected to be used in the coming decade on short haul flights with narrow-body aircraft.

Files

Master_Thesis_Merijn_van_Holst... (.pdf)
(.pdf | 7.59 Mb)
- Embargo expired in 19-09-2021