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针对自适应循环发动机(ACE)的一种布局形式,利用所建立的部件级性能仿真模型,对其多种工作模式下典型工作点的匹配机理及工作特性进行仿真和分析。研究结果表明,节流比TR选择对地面起飞推重比和高空高速性能均产生较大影响;可变Flade风扇的出现使得发动机从不加力向加力模式转变时可采用固定的喷口喉道面积;通过多个可调几何的协同调节,ACE发动机循环模式的选择具有更多的灵活性,总涵道比的变化幅度更大(0.28～1.43,地面起飞工作点);相同的推力水平下,与单涵模式相比,三涵模式的单位耗油率在亚声巡航工作点(H=11km,Ma=0.8)大约降低9.1%,在超声巡航工作点(H=11km,Ma=1.5)大约降低2.3%。
Aiming at the layout of adaptive cycle engine (ACE), the simulation and analysis of the matching mechanism and working characteristic of the typical working point under various working modes are carried out by using the established component level performance simulation model. The results show that throttling ratio TR selection has a greater impact on ground takeoff thrust-weight ratio and high-altitude high-speed performance. The appearance of variable Flade fan makes it possible to use a fixed nozzle throat area ; Through coordination of multiple adjustable geometries, the choice of ACE engine cycle mode has more flexibility and greater change of total bypass ratio (0.28 ~ 1.43, ground take-off operating point); under the same thrust level, Compared with the single-Han model, the unit fuel consumption of Sam Han model decreased by about 9.1% at subsonic cruise operation (H = 11km, Ma = 0.8) and about 10% at ultrasonic cruise operation Reduce by 2.3%.