Simulation and analysis of an ammonia-SOFC integrated aero engine show that specific impulse can achieve 42% of conventional airliner turbofan engines at cruise conditions, whereas the specific thrust is significantly higher at 213%. The modelled engine has a reduced bypass ratio and increased fan pressure ratio to fit the operation conditions of the SOFC and heat exchange systems consisting of an intercooler and a turbine recuperator. The compressor bleed air is cooled to enhance turbine cooling. Sensitivity analysis of the baseline case suggests modification toward a higher fan pressure ratio, smaller compressor pressure ratio and bypass ratio can further optimize the performance. The adjustment of the SOFC fuel utilization ratio can help engine thrust control. The compatibility of ammonia-based hybrid engines with medium-range, medium-size platforms is shown.
Xu et al. (Mon,) studied this question.