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Basic Comparison of Three Aircraft Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Basic Comparison of Three Aircraft Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion 1 Master Thesis Basic Comparison of Three Aircraft Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion Author: Clinton Rodrigo Supervisor: Prof. Dr.-Ing. Dieter Scholz, MSME Submitted: 2019-09-22 Faculty of Engineering and Computer Science Department of Automotive and Aeronautical Engineering 2 DOI: https://doi.org/10.15488/9329 URN: https://nbn-resolving.org/urn:nbn:de:gbv:18302-aero2019-09-22.014 Associated URLs: https://nbn-resolving.org/html/urn:nbn:de:gbv:18302-aero2019-09-22.014 © This work is protected by copyright The work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License: CC BY-SA https://creativecommons.org/licenses/by-sa/4.0 Any further request may be directed to: Prof. Dr.-Ing. Dieter Scholz, MSME E-Mail see: http://www.ProfScholz.de This work is part of: Digital Library - Projects & Theses - Prof. Dr. Scholz http://library.ProfScholz.de Published by Aircraft Design and Systems Group (AERO) Department of Automotive and Aeronautical Engineering Hamburg University of Applied Science This report is deposited and archived: Deutsche Nationalbiliothek (https://www.dnb.de) Repositorium der Leibniz Universität Hannover (https://www.repo.uni-hannover.de) Internet Archive (https://archive.org) Item: https://archive.org/details/TextRodrigo.pdf This report has associated published data in Harvard Dataverse: https://doi.org/10.7910/DVN/K5FLHR 3 Abstract Purpose – This paper presents a comparison of aircraft design concepts to identify the superior propulsion system model among turbo-hydraulic, turbo-electric and classic jet propulsion with respect to Direct Operating Costs (DOC), environmental impact and fuel burn. Approach – A simple aircraft model was designed based on the Top-Level Aircraft Requirements of Airbus A320 passenger aircraft, and novel engine concepts were integrated to establish new models. Numerous types of propulsion system configurations were created by varying the type of gas turbine engine and number of propulsors. Findings – After an elaborate comparison of the aforementioned concepts, the all turbo- hydraulic propulsion system is found to be superior to the all turbo-electric propulsion system. A new propulsion system concept was developed by combining the thrust of a turbofan engine and utilizing the power produced by the turbo-hydraulic propulsion system that is delivered via propellers. The new partial turbo-hydraulic propulsion concept in which 20% of the total cruise power is coming from the (hydraulic driven) propellers is even more efficient than an all turbo-hydraulic concept in terms of DOC, environmental impact and fuel burn. Research Limitations – The aircraft were modelled with a spreadsheet based on handbook methods and relevant statistics. The investigation was done only for one type of reference aircraft and one route. A detailed analysis with a greater number of reference aircraft and types of routes could lead to other results. Practical Implications – With the provided spreadsheet, the DOC and environmental impact can be approximated for any commercial reference aircraft combined with the aforementioned propulsion system concepts. Social Implications – Based on the results of this thesis, the public will be able to discuss the demerits of otherwise highly lauded electric propulsion concepts. Value – To evaluate the viability of the hydraulic propulsion systems for passenger aircraft using simple mass models and aircraft design concept. 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