超声速民机因其在长距离、长航时航线运输方面所具有的明显优势，已成为未来民机的重要发展方向。“绿色航空”概念的提出使得节能减排和降噪越来越成为民机的重要优化设计目标之一，自然对其动力装置也提出了相应的要求。传统构型动力无法实现起飞低噪声、超巡高单位推力、低耗油率和低排放指标的兼顾。以带核心机驱动风扇级（CDFS）的双外涵变循环发动机（VCE）构型为研究对象，考虑发动机性能及喷流噪声、NO _x 排放等关键优化设计目标，开展稳态可调几何控制规律设计方法研究。研究表明，提高第1外涵分流比有助于降低NO _x 排放，提高内涵和第2外涵分流比有助于降低喷流噪声。将设计结果应用于第1代超声速客机“协和号”动力装置重优化设计，与基准方案相比，在满足飞机性能需求的前提下，超声速巡航工况耗油率降低了20.19%，起飞工况喷流速度实现了44.47%的降幅，使得起飞噪声指标满足适航要求。

Due to its prominent advantages in long-distance and long-endurance transportation， supersonic civil aircraft has become an important development direction for future civil aircraft. The concept of “green aviation” makes energy saving， emission reduction and noise reduction important optimization design objectives of civil aircraft， which naturally imposes corresponding requirements for its power plant. The traditional configuration power fails to realize the combination of low noise at takeoff， high thrust per unit for super-cruise， low fuel consumption rate and low emission index. Taking the dual-containment Variable Cycle Engine（VCE） configuration with Core Driven Fan Stage（CDFS） as the research object， this study examines the design method of steady state adjustable geometry control law considering key optimization design objectives such as the engine performance， jet noise， and NO _x emission. The research shows that the improvement in the first-containment variable cycle engine is the best way to improve the engine performance， and increase in the first culvert split ratio helps to reduce NO _x emission， while increase in the inner and second culvert split ratios facilites jet noise reduction. The design results are applied to the power unit re-optimization design of the first generation supersonic airliner Concorde. Compared with the baseline scheme， the supersonic cruise fuel consumption rate and the takeoff jet speed are reduced by 20.19% and 44.47%， respectively， enabling the takeoff noise index to meet the airworthiness requirements， under the premise of fulfilling the performance requirements of the aircraft.