Thermodynamic Performance Comparisons of Ideal Brayton Cycles Integrated with High Temperature Fuel Cells as Power Sources on Aircraft

Developing hybrid electric aircraft is propitious to reducing carbon dioxide emissions and fuel consumption. Combustion engines coupled with solid oxide cells are proposed for propulsion systems, where the compressor powered by instead of turbines. The thermal cycle new engine obviously different from that conventional combustion can be characterized in temperature entropy diagram under some reasonable assumptions, which were analyzed investigated. Performance parameters, such as specific thrust, derived expressed several fundamental parameters. Three cycles integrating Brayton SOFC shown. main conclusions follows: (1) maximum operating pressure ratio integrated 32. efficiency at lowest 82.2%, while BC 65.1% high temperature. (2) not work if lower than 1350 K. Otherwise, utilization will too huge.