Details
| Originalsprache | Englisch |
|---|---|
| Aufsatznummer | 012101 |
| Seitenumfang | 7 |
| Fachzeitschrift | Journal of Physics: Conference Series |
| Jahrgang | 2766 |
| Frühes Online-Datum | 3 Juni 2024 |
| Publikationsstatus | Veröffentlicht - 2024 |
| Veranstaltung | 9th European Thermal Sciences Conference, EUROTHERM 2024 - Bled, Slowenien Dauer: 10 Juni 2024 → 13 Juni 2024 |
Abstract
Fully electric propulsion systems integrating hydrogen-powered fuel cells and batteries are promising options to reduce the overall climate impact of regional aircraft. However, the increase in low-temperature heat sources aboard the aircraft calls for advanced thermal management system solutions. To address this challenge, this study presents a sizing methodology for ram air heat exchangers in the nacelle-integrated cooling loop of an all-electric regional aircraft based on the ATR-72 platform. Different discretization schemes are compared to identify an optimal sizing method. The results highlight the simplicity and efficiency of the 0D ϵ-NTU model. Geometric design variables are optimized with respect to drag and mass during a hot-day take-off. The resulting Pareto front reveals a tendency for low airflow outlet temperatures and large diffuser area ratios to result in lightweight designs but in turn, induce high drag and require a large installation space. Comparative analyses of specific optimal ram air duct designs and equivalent skin heat exchangers demonstrate the potential of a second heat sink over a flight mission. The limited heat transfer area of the skin heat exchanger proves insufficient for hot-day take-off and climb but offers advantages during cruise and descent thanks to the reduced drag.
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in: Journal of Physics: Conference Series, Jahrgang 2766, 012101, 2024.
Publikation: Beitrag in Fachzeitschrift › Konferenzaufsatz in Fachzeitschrift › Forschung › Peer-Review
}
TY - JOUR
T1 - Physically based heat exchanger sizing method for the thermal management system of all-electric regional aircraft
AU - Nozinski, Marius
AU - Benam, Behnam Parizad
AU - Servi, Carlo De
AU - Kabelac, Stephan
AU - Falsetti, Chiara
N1 - Publisher Copyright: © Published under licence by IOP Publishing Ltd.
PY - 2024
Y1 - 2024
N2 - Fully electric propulsion systems integrating hydrogen-powered fuel cells and batteries are promising options to reduce the overall climate impact of regional aircraft. However, the increase in low-temperature heat sources aboard the aircraft calls for advanced thermal management system solutions. To address this challenge, this study presents a sizing methodology for ram air heat exchangers in the nacelle-integrated cooling loop of an all-electric regional aircraft based on the ATR-72 platform. Different discretization schemes are compared to identify an optimal sizing method. The results highlight the simplicity and efficiency of the 0D ϵ-NTU model. Geometric design variables are optimized with respect to drag and mass during a hot-day take-off. The resulting Pareto front reveals a tendency for low airflow outlet temperatures and large diffuser area ratios to result in lightweight designs but in turn, induce high drag and require a large installation space. Comparative analyses of specific optimal ram air duct designs and equivalent skin heat exchangers demonstrate the potential of a second heat sink over a flight mission. The limited heat transfer area of the skin heat exchanger proves insufficient for hot-day take-off and climb but offers advantages during cruise and descent thanks to the reduced drag.
AB - Fully electric propulsion systems integrating hydrogen-powered fuel cells and batteries are promising options to reduce the overall climate impact of regional aircraft. However, the increase in low-temperature heat sources aboard the aircraft calls for advanced thermal management system solutions. To address this challenge, this study presents a sizing methodology for ram air heat exchangers in the nacelle-integrated cooling loop of an all-electric regional aircraft based on the ATR-72 platform. Different discretization schemes are compared to identify an optimal sizing method. The results highlight the simplicity and efficiency of the 0D ϵ-NTU model. Geometric design variables are optimized with respect to drag and mass during a hot-day take-off. The resulting Pareto front reveals a tendency for low airflow outlet temperatures and large diffuser area ratios to result in lightweight designs but in turn, induce high drag and require a large installation space. Comparative analyses of specific optimal ram air duct designs and equivalent skin heat exchangers demonstrate the potential of a second heat sink over a flight mission. The limited heat transfer area of the skin heat exchanger proves insufficient for hot-day take-off and climb but offers advantages during cruise and descent thanks to the reduced drag.
UR - http://www.scopus.com/inward/record.url?scp=85195597882&partnerID=8YFLogxK
U2 - 10.1088/1742-6596/2766/1/012101
DO - 10.1088/1742-6596/2766/1/012101
M3 - Conference article
AN - SCOPUS:85195597882
VL - 2766
JO - Journal of Physics: Conference Series
JF - Journal of Physics: Conference Series
SN - 1742-6588
M1 - 012101
T2 - 9th European Thermal Sciences Conference, EUROTHERM 2024
Y2 - 10 June 2024 through 13 June 2024
ER -