氢能民用涡扇发动机总体性能建模与分析

For the potential application of hydrogen with zero-carbon emission and high energy density in the field of aeroengine power, this study constructs two thermal cycle models of hydrogen civil turbofan engine : direct fuel replacement type and water enhanced cycle type, and systematically compares the performance differences in equal thrust, equal pre-turbine temperature and equal core engine mass flow conditions. The study shows that by using hydrogen as fuel, the overall engine performance can be improved by about 5%, which verifies the feasibility of using hydrogen directly in existing aviation kerosene engines without changing the structure of components. For the water-enhanced turbofan engine, the exhaust water vapor recovery needs to reach 28% to have an energy consumption advantage. When the percentage of water vapor recovery reaches 50%, the combustion chamber outlet temperature can be reduced by 123 K, the thrust can be increased by 22.9%, and the energy consumption can be reduced by 14.6%. The analysis shows that, to fully utilize the advantages of the water-enhanced turbofan engine, it is necessary to adopt a large bypass ratio, while increasing the limit of the pre-turbine temperature and increasing the water vapor recovery percentage (up to 50%) . This study reveals the gain mechanism of the hydrogen application on the overall performance of the turbofan engine, which provides theoretical support for the selection of future hydrogen power systems.