三种自适应循环发动机总体性能优化对比

Based on flight mission demand of supersonic civil transport， three configurations of adaptive cycle engines were selected as candidate propulsion systems and comparison of overall performance optimization was carried out. Numerical simulation model and mathematical optimization model for overall performance were established. The criteria for selecting design cycle parameters were determined. Performance optimization comparisons of three adaptive cycle engines in typical working conditions were conducted， and performance of the engine under high power demand and low fuel consumption demand conditions were analyzed. Based on the analysis results，the optimal configuration was selected and the design cycle parameters were optimized based on flight mission demand. The results indicate that mode transition can significantly expand the thrust range and reduce fuel consumption. For instance， in Configuration A， the thrust range is broadened by approximately 14.14% and the fuel consumption is reduced by about 5.75% during subsonic cruise. Configuration A exhibits a fuel consumption advantage during subsonic cruise，and has large take-off thrust. Configuration B shows a fuel consumption advantage at the initial segment of the throttle characteristic curve during supersonic cruise，and is suitable for aircraft with high take-off weights. Configuration C demonstrates low fuel consumption in both subsonic and supersonic cruise， and is suitable for smaller supersonic passenger aircraft. By optimizing the design cycle parameters of Configuration C，the aircraft’s take-off weight can be increased by 3.62%，and specific fuel consumption during supersonic cruise can be reduced by approximately 3%，which benefit for passenger capacity and flight range.