質量・体積制約下での固体酸化物燃料電池統合ターボファンエンジンの多目的最適化：民間低炭素航空機向け
Multidisciplinary Optimization of a Turbofan Engine Integrated with Solid Oxide Fuel Cells Under Mass and Volume Constraints for Civil Low-Carbon Aircraft (原題)
Zhenyu Shen, Zhixing Ji
🤖 gxceed AI 要約
日本語
本論文は、固体酸化物燃料電池（SOFC）をターボファンエンジンに統合したハイブリッド推進システムを提案し、質量・体積・熱力学性能を考慮した多次元モデルを構築した。等価比と分流比が体積・質量比に強く影響し、効率は約63%が上限であることを示した。多目的最適化により、CFM56 3C1と比較して熱効率21%向上、推進効率42%向上を達成した。
English
This paper proposes a hybrid propulsion system integrating solid oxide fuel cells (SOFC) with a turbofan engine, establishing a multidimensional model considering mass, volume, and thermodynamic performance. It finds that equivalence ratio and split ratio strongly influence volume and mass ratios, with maximum overall efficiency around 63%. Multi-objective optimization achieves 21% higher thermal efficiency and 42% higher propulsion efficiency compared to CFM56 3C1.
Unofficial AI-generated summary based on the public title and abstract. Not an official translation.
📝 gxceed 編集解説 — Why this matters
日本のGX文脈において
日本の航空機産業では、次世代航空機の脱炭素化が課題であり、水素・電動推進技術の研究が進む。本論文はSOFC統合による効率向上を示し、国産技術開発の参考となる。また、航空機の軽量化は燃費改善に直結し、日本の部材メーカーにも示唆を与える。
In the global GX context
Globally, aviation decarbonization is a critical challenge, with hydrogen and electric propulsion being key pathways. This paper contributes to the literature on hybrid-electric aircraft by demonstrating the potential of SOFC integration to improve efficiency, relevant to international efforts to reduce aviation emissions.
👥 読者別の含意
🔬研究者:Provides a novel modeling approach for SOFC-turbofan hybrid engines, useful for further optimization studies.
🏢実務担当者:Offers insights into the trade-offs between efficiency and mass/volume constraints, informing design decisions for hybrid propulsion systems.
📄 Abstract（原文）
Mass and volume penalties associated with fuel cell integration have hindered the manufacturing and integration of hybrid power systems into civil aircraft. To address this issue, a novel scheme, a turbofan engine integrated with solid oxide fuel cells, is proposed in this paper, which has the advantage of high thermal efficiency and propulsion efficiency, where the electricity produced by the solid oxide fuel cell (SOFC) is used to drive the ducted fan. Then, a multidimensional model that accounts for mass, volume, and thermodynamic performance is established. The equivalence ratio and split ratio have a significantly stronger influence on the volume and mass ratios than the current density. These two parameters directly determine the power ratio between the fuel cell and the gas turbine. An increase in the power ratio leads to a simultaneous rise in both the volume and mass ratios; however, the overall efficiency cannot be continuously improved, with its maximum value being approximately 63% without mass and volume constraints. During the multi-objective optimization process, the weight and volume of the hybrid engine have a linear relationship with the overall efficiency when the efficiency is lower than 50%. However, both mass and volume exhibit exponential increasing trends as the overall efficiency is over 50%. This is caused by the nonlinear change in the fuel cell reaction area; as polarization loss decreases, the thermal efficiency of the hybrid system improves. The maximum overall efficiency is taken as the optimization objective, with the constraints that the mass fraction of the fuel cell does not exceed 0.4 of the total engine mass and that the volume fraction of the fuel cell stack is less than 0.2 of the gas turbine engine volume. Compared with the CFM56 3C1, the thermal efficiency for the novel hybrid engine is increased by 21%, and its propulsion efficiency is increased by 42%.
🔗 Provenance — このレコードを発見したソース
- openalex https://doi.org/10.3390/aerospace13090814first seen 2026-09-09 04:59:34
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