This paper concerns a solid oxide fuel cell (SOFC) based integrated powering system for a medium‐sized airplane and analyzes it thermodynamically for its performance assessment and evaluation. It further investigates the system in relation to aircraft operating conditions and provides the conceptual solutions for heating and cooling at various temperatures. The results of the energy and exergy analyses and performance assessments of the proposed integrated system are presented and discussed. The exergy and energy efficiencies of the main components are calculated and observed for the SOFCs with the maximum values of 84.54% and 80.31%, respectively. The present integrated system has overall energy and exergy efficiencies of 57.53% and 47.18%, respectively. Furthermore, it is found that an increase in the reforming temperature ratio can improve the hydrogen yield. However, when the system is operated at a temperature higher than 800°C, the hydrogen yield decreases since a reverse water gas shift reaction is more pronounced. Moreover, the SOFC shows the best performance at 800°C with a maximum power density of 1.23 W/cm².

中文翻译：

---

中型飞机集成固体氧化物燃料电池系统的开发和评估

本文涉及一种用于中型飞机的基于固体氧化物燃料电池（SOFC）的集成动力系统，并对其进行热力学分析以对其性能进行评估和评估。它进一步研究了与飞机运行状况有关的系统，并提供了在各种温度下进行加热和冷却的概念性解决方案。提出并讨论了所提出的集成系统的能量和火用分析结果以及性能评估。计算并观察了SOFC的主要成分的火用和能量效率，其最大值分别为84.54％和80.31％。本集成系统的总能量和火用效率分别为57.53％和47.18％。此外，发现提高重整温度比可以提高氢产率。然而，当该系统在高于800℃的温度下操作时，氢的产率降低，因为逆水煤气变换反应更明显。此外，SOFC在800°C时表现出最佳性能，最大功率密度为1.23 W / cm²。