DC/DC-converter for fuel cell integration in more electric aircraft applications

Warncke, M.; Fahlbusch, Sebastian; Hoffmann, Klaus F.

doi:10.23919/epe17ecceeurope.2017.8099134

Cited by 7 publications

(4 citation statements)

References 2 publications

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“…The authors have not been able to find published performance metrics on DC/DC converters operating at cryogenic temperatures. Warncke et al [34] have published results on a conventionally cooled DC/DC converter for aircraft applications. They have achieved a power density of 8.3 kW/kg for the power module alone, which is similar to what can be achieved for an optimized motor inverter with current conventional technology [35].…”

Section: G Fuel Cell Dc/dc Converter Sizingmentioning

confidence: 99%

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: G Fuel Cell Dc/dc Converter Sizingmentioning

confidence: 99%

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.

View full text Add to dashboard Cite

show abstract

“…The authors have not been able to find published performance metrics on DC/DC converters operating at cryogenic temperatures. Warncke et al [32] have published results on a conventionally cooled DC/DC converter for aircraft applications. They have achieved a power density of 8.3 kW/kg for the power module alone, which is similar to what can be achieved for an optimized motor inverter with current conventional technology [33].…”

Section: G Fuel Cell Dc/dc Converter Sizingmentioning

confidence: 99%

Conceptual Design, Sizing and Performance Analysis of a Cryo-Electric Propulsion System for a Next-Generation Hydrogen-Powered Aircraft

Hartmann¹,

Nøland²,

Nilssen³

et al. 2021

Preprint

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In this paper, we present a comprehensive sizing and performance analysis 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\textsubscript{2}) fuel to provide cryogenic cooling to the electric propulsion system, and thereby enable ultra-compact 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 analysis shows 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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“…A non-isolated topology could be used to integrate the sources into the electrical power supply system. In publications [69] and [103] on a MEA and a fuel cell-powered small electric aircraft, step-up converters are used. The converter for the battery has to be bidirectional to enable charging and discharging, while the converter connecting the fuel cell can be unidirectional [69], [103].…”

Section: ) Non-isolated Convertersmentioning

confidence: 99%

Discussion on Electric Power Supply Systems for All Electric Aircraft

et al. 2020

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The electric power supply system is one of the most important research areas within sustainable and energy-efficient aviation for more-and especially all electric aircraft. This paper discusses the history in electrification, current trends with a broad overview of research activities, state of the art of electrification and an initial proposal for a short-range aircraft. It gives an overview of the mission profile, electrical sources, approaches for the electrical distribution system and the required electrical loads. Current research aspects and questions are discussed, including voltage levels, semiconductor technology, topologies and reliability. Because of the importance for safety possible circuit breakers for the proposed concept are also presented and compared, leading to a initial proposal. Additionally, a very broad review of literature and a state of the art discussion of the wiring harness is given, showing that this topic comes with a high number of aspects and requirements. Finally, the conclusion sums up the most important results and gives an outlook on important future research topics. INDEX TERMS Aviation, aerospace electronics, MEA, AEA, electric power supply systems, dc-dc power converters, power semiconductor devices, wide bandgap semiconductors, high voltage direct current (HVDC), circuit breaker, hybrid circuit breaker.

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DC/DC-converter for fuel cell integration in more electric aircraft applications

Cited by 7 publications

References 2 publications

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

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

Conceptual Design, Sizing and Performance Analysis of a Cryo-Electric Propulsion System for a Next-Generation Hydrogen-Powered Aircraft

Discussion on Electric Power Supply Systems for All Electric Aircraft

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