Optimal operating conditions of PEM fuel cells in commercial aircraft

Schröder, M.; Becker, Florian; Kallo, Josef; Gentner, Christoph

doi:10.1016/j.ijhydene.2021.07.099

Cited by 34 publications

(37 citation statements)

References 56 publications

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“…The PEMFC mass estimate is based on the weight of the fuel cell stack, the compressor, and the humidifier. This is in accordance with the approach of Schröder et al [1]. Additionally, a mass overhead is added to account for the remaining balance of plant (BoP) components, structural materials, etc.…”

Section: ) Mass Estimatesmentioning

confidence: 98%

“…Numerous studies have been performed on the components that together constitute the full system [1], [9]- [12], but these studies are either conducted on other system architectures or on single components that overlooks the important system considerations. The concept of using hydrogen for cryogenic cooling has also been investigated in detailed studies, e.g.…”

Section: Airmentioning

confidence: 99%

“…In addition to the compressor and heat exchanger (FCHX) already described, the system comprises an air inlet diffuser, a humidifier, and balance-of-plant (BoP) components. The operating parameters, shown in green, are adopted from reference [1].…”

Section: H Pem Fuel Cell Sizingmentioning

confidence: 99%

“…The stoichiometric ratio λ O2 on the cathode side is also greater than one. The stoichometric ratios used in this paper are adopted from Schröder et al [1]. There, a net stoichiometric ratio of λ H2,net = 1.05 is achieved through hydrogen recirculation.…”

Section: ) Stoichiometric Ratiosmentioning

confidence: 99%

“…Eqs. ( 20) through (24) have been adopted from Schröder et al [1], [40], [41]. For simplicity, the input filter has been omitted from the model.…”

Section: ) Compressor Powermentioning

confidence: 99%

See 4 more Smart Citations

Dual Use of Liquid Hydrogen in a Next-Generation PEMFC-Powered Regional Aircraft With Superconducting Propulsion

Hartmann

Nøland

Nilssen

et al. 2022

IEEE Trans. Transp. Electrific.

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In this paper, we present a comprehensive model framework for a disruptive cryo-electric propulsion system intended for a hydrogen-powered regional aircraft. The main innovation lies in the systematic treatment of all the electrical and thermal components to model the overall system performance. One of the main objectives is to study the feasibility of using the liquid hydrogen (LH 2 ) fuel to provide cryogenic cooling to the cryo-electric propulsion system, and thereby enable ultracompact designs. Another aim has been to identify the optimal working point of the fuel cell to minimize the overall propulsion system's mass. The full mission profile is evaluated to make the analysis as realistic as possible. Analyses are done for three different 2035 scenarios, where available data from the literature are projected to a baseline, conservative, and optimistic scenario. The results show that the total propulsion system's power density can be as high as 1.63 kW/kg in the optimistic scenario and 0.79 kW/kg in the baseline scenario. In the optimistic scenario, there is also sufficient cryogenic cooling capacity in the hydrogen to secure proper conditions for all components, whereas the DC/DC converter falls outside the defined limit of 110 K in the baseline scenario.

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Section: ) Mass Estimatesmentioning

confidence: 98%