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Design of a Direct-Liquid-Cooled Motor and Operation Strategy for the Cooling System

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  • Ralf Johannes Keuter

    (Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38106 Brauschweig, Germany
    Institute for Drive Systems and Power Electronics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

  • Florian Niebuhr

    (Institute for Drive Systems and Power Electronics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

  • Marius Nozinski

    (Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38106 Brauschweig, Germany
    Institute for Thermodynamics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

  • Eike Krüger

    (Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38106 Brauschweig, Germany
    Institute for Drive Systems and Power Electronics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

  • Stephan Kabelac

    (Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38106 Brauschweig, Germany
    Institute for Thermodynamics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

  • Bernd Ponick

    (Cluster of Excellence SE2A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38106 Brauschweig, Germany
    Institute for Drive Systems and Power Electronics, Leibniz Universität Hannover, 30823 Garbsen, Germany)

Abstract

To make an all-electric aircraft possible, both high power densities and efficiencies are needed. However, particularly high demands are also placed on the thermal management system. Often, the electric motor and cooling system are considered without co-optimization. Particularly in the case of electric motors with conductors directly cooled by a liquid, there is great potential for optimization, since the temperature-dependent Joule losses determine the largest part of the losses. This publication shows the main influencing parameters for the electric motor and cooling system: coolant speed and winding temperature. In addition, the influence of the cooling system control during a flight mission is demonstrated and its potential in mass reduction is quantified. It could be shown that with a low utilized electric motor the maximum winding temperature of 130 ° C is beneficial, the cooling system should work in almost all operation points in its sized operation and the mass of the heat exchanger and pump is negligible compared to the mass of the electric motor and energy storage.

Suggested Citation

  • Ralf Johannes Keuter & Florian Niebuhr & Marius Nozinski & Eike Krüger & Stephan Kabelac & Bernd Ponick, 2023. "Design of a Direct-Liquid-Cooled Motor and Operation Strategy for the Cooling System," Energies, MDPI, vol. 16(14), pages 1-14, July.
    • Handle: RePEc:gam:jeners:v:16:y:2023:i:14:p:5319-:d:1191964
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    References listed on IDEAS

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    1. David C. Deisenroth & Michael Ohadi, 2019. "Thermal Management of High-Power Density Electric Motors for Electrification of Aviation and Beyond," Energies, MDPI, vol. 12(19), pages 1-18, September.
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    Cited by:

    1. Sangyoon Lee & Sangook Jun & Jae-Sung Huh & Poomin Park & Byeung-Jun Lim, 2024. "Inclined Installation Effect on the Offset Strip Finned Heat Exchanger Designed for a Hybrid Electric Propulsion System in Electric Vertical Take-Off and Landing," Energies, MDPI, vol. 17(19), pages 1-17, October.

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