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Novel hybrid aircraft propulsion systems using hydrogen, methane, methanol, ethanol and dimethyl ether as alternative fuels

机译：新颖的杂种飞机推进系统，使用氢，甲烷，甲醇，乙醇和二甲醚作为替代燃料

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This paper presents a unique hybrid type aircraft propulsion system which combines a commercial turbofan system with a solid oxide fuel cell system. Thermodynamic analyses and parametric studies are collectively performed to investigate the compatibility and applicability of the proposed system as well as its performance through the energetic and exergetic efficiencies to determine how the efficiencies are affected by varying the operating conditions. Hydrogen, methane, methanol, ethanol, and dimethyl ether with different combinations are chosen as alternative fuels to replace kerosene, which is a traditional, fossil-based fuel. It is found that the net power of the solid oxide fuel cell is 944 kW with an electric efficiency of 87.0%. A maximum thermal efficiency of 32.3% and exergetic efficiency of 43.9% were achieved using 75% methane and 25% hydrogen fuel. The maximum overall thermal and exergetic efficiencies of the hybrid turbofan are 48.1% and 54.4%, respectively, using 75% methanol and 25% hydrogen fuel, which reduce carbon emissions by 65% compared to the fossil fuels. Therefore, the hybrid turbofan aircraft engine can increase the turbofan performance. In addition, a fuel mixture of 60% ethanol and 40% hydrogen can increase the performance by 5% and reduce carbon emissions by 73%.
机译：本文介绍了一种独特的混合型飞机推进系统，将商用涡多孔系统与固体氧化物燃料电池系统相结合。集体进行热力学分析和参数研究，以研究所提出的系统的兼容性和适用性，以及通过能量和前进效率的性能，以确定如何通过改变操作条件来影响效率的影响。选择具有不同组合的氢，甲烷，甲醇，乙醇和二甲醚作为替代燃料，以替代煤油，这是一种传统的化石燃料。发现固体氧化物燃料电池的净功率为944kW，电效率为87.0％。使用75％甲烷和25％的氢燃料，实现了32.3％的最大热效率为32.3％和43.9％。杂交涡轮机的最大总热量和横渗效率分别使用75％甲醇和25％氢燃料，分别为48.1％和54.4％，与化石燃料相比，将碳排放量减少65％。因此，混合动力涡轮机飞机发动机可以提高涡轮机的性能。此外，60％乙醇和40％氢气的燃料混合物可将性能提高5％并降低碳排放量73％。

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