Details
| Original language | English |
|---|---|
| Article number | 5319 |
| Journal | ENERGIES |
| Volume | 16 |
| Issue number | 14 |
| Publication status | Published - 12 Jul 2023 |
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 (Formula presented.) 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.
Keywords
- aircraft propulsion, all-electric aircraft, coolant velocity, electric aircraft, electric propulsion system, permanent magnet synchronous motor, winding temperature
ASJC Scopus subject areas
- Energy(all)
- Renewable Energy, Sustainability and the Environment
- Energy(all)
- Fuel Technology
- Engineering(all)
- Engineering (miscellaneous)
- Energy(all)
- Energy Engineering and Power Technology
- Energy(all)
- Energy (miscellaneous)
- Mathematics(all)
- Control and Optimization
- Engineering(all)
- Electrical and Electronic Engineering
Sustainable Development Goals
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In: ENERGIES, Vol. 16, No. 14, 5319, 12.07.2023.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Design of a Direct-Liquid-Cooled Motor and Operation Strategy for the Cooling System
AU - Keuter, Ralf Johannes
AU - Niebuhr, Florian
AU - Nozinski, Marius
AU - Krüger, Eike
AU - Kabelac, Stephan
AU - Ponick, Bernd
N1 - Funding Information: This research was funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation) under Germany’s Excellence Strategy EXC 2163/1. Sustainable and Energy Efficient Aviation Project ID 390881007. https://www.tu-braunschweig.de/se2a (accessed on 1 January 2019).
PY - 2023/7/12
Y1 - 2023/7/12
N2 - 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 (Formula presented.) 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.
AB - 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 (Formula presented.) 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.
KW - aircraft propulsion
KW - all-electric aircraft
KW - coolant velocity
KW - electric aircraft
KW - electric propulsion system
KW - permanent magnet synchronous motor
KW - winding temperature
UR - http://www.scopus.com/inward/record.url?scp=85166265836&partnerID=8YFLogxK
U2 - 10.3390/en16145319
DO - 10.3390/en16145319
M3 - Article
AN - SCOPUS:85166265836
VL - 16
JO - ENERGIES
JF - ENERGIES
SN - 1996-1073
IS - 14
M1 - 5319
ER -