液氨-航空煤油化学回热燃料电池/涡轴发动机混合动力系统的设计与性能评估

To address the growing demand for carbon reduction in the aviation sector，a liquid ammonia-kerosene chemical recuperation fuel cell/turboshaft hybrid system is proposed in this paper. This hybrid system utilizes the efficient fuel cell to drive the compressor，achieving decoupling between the turbine and compressor，while enabling hydrogen production via ammonia chemical recuperation. The configuration differs from conventional hybrid systems，making it particularly suitable for aviation applications. In this study，the hybrid system design and performance evaluation were conducted using a thermodynamic model. The results show that higher excess air coefficients and ammonia decomposition temperatures contribute to improved fuel economy and enhanced carbon reduction effects in the hybrid system. However，fuel utilization rates should be selected to balance fuel consumption requirements with carbon reduction objectives. The comparative analysis results indicate that the hybrid system demonstrates significant advantages in thermal efficiency，propulsion efficiency，and overall efficiency，with an increase of over 40% in overall efficiency compared to conventional turboshaft engines. Under the same output power，the hybrid system achieves an 87.46% reduction in carbon emissions at the cost of increasing fuel consumption by 44.96%. In contrast，under equivalent turbine inlet temperatures，the hybrid system achieves a 43.99% reduction in carbon emissions at the cost of increasing fuel consumption by 16.49%. Overall，this program achieves a substantial reduction in carbon emissions with minimal performance trade-offs，demonstrating high feasibility for application.