固体氧化物燃料电池
氢燃料强化
氢燃料
气体压缩机
飞机燃油系统
燃烧
制动比油耗
涡轮机
回热器
燃料质量分数
核工程
环境科学
燃料气
汽车工程
燃油喷射
工艺工程
工程类
燃烧室
内燃机
机械工程
蒸汽锁
化学
燃料电池
化学工程
热交换器
物理化学
阳极
有机化学
电极
作者
Lauren N. Rupiper,Brent B. Skabelund,Rhushikesh Ghotkar,Ryan J. Milcarek
标识
DOI:10.1016/j.seta.2022.101959
摘要
This study investigates the performance of a flame-assisted fuel cell integrated with a gas turbine operating with six fuels (CH4, C3H8, JP-4, JP-5, JP-10, and H2). A thermodynamic model is developed for the fuel-rich combustion, fuel-lean combustion and each step of the gas turbine including the compressor, turbine and recuperator in order to analyze the overall hybrid gas turbine cycle. As the fuel/air equivalence ratio increases, the hybrid system efficiency increases initially then decreases despite increasing hydrogen concentration in the exhaust. The peak efficiency occurs around an equivalence ratio of 2 for all fuels. The optimal performance of the hybrid system utilizes H2 as the fuel. The peak electrical efficiency of the hybrid setup is 64.7% with H2 fuel, 60.3% with CH4 fuel, 60.9% with C3H8 fuel, 61.7% with JP-4 fuel, 61.0% with JP-5 fuel and 61.2% with JP-10 fuel, representing a significant increase over the standard gas turbine cycle. With H2 fuel, the overall integrated system is predicted to be 24.5% more efficient than the standard gas turbine system. These results show promise for a fuel flexible hybrid gas turbine which could benefit the growing aircraft industry as the desire for a more electric airplane increases.
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