Modeling and analysis of distributed propulsion system based on gas-driven multi-fans

A distributed propulsion system based on gas-driven multi-fans, named the gas-driven distributed propulsion system (GDDPS), was investigated through modelling, parameter analysis, and comparison with turbo-electric distributed propulsion (TeDP). The results of the parameter analysis reveal the optimal matching relationship between design parameters and the impact of the heat exchanger on the propulsion system's performance. The characteristics of the thermodynamic cycle of the propulsion system were obtained through comparison with TeDP system. The matching relationship between the propulsor fan and power turbine was studied, demonstrating that the usage of a reduction drive is necessary. Then, the performance characteristics at different operating conditions were obtained. After that, the propulsion system was designed based on the requirements of traditional civil aircraft, and the design results were also compared with TeDP and a traditional turbofan engine. Results demonstrate that while both the GDDPS and TeDP systems exhibit performance improvements over conventional propulsion, the fuel consumption of GDDPS is 5.7% lower than that of TeDP, and the specific thrust is 6.1% higher. These findings substantiate the technical viability of GDDPS for reducing aviation fuel consumption and provide a reference for the design of a distributed propulsion system.