| 摘要: |
| 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%。 |
| 关键词: 自适应循环发动机 仿真 推重比 节流比 性能 |
| DOI： |
| 分类号: |
| 基金项目:国家青年科学基金(51206005)。 |
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| Steady Performance Investigation on Various Modes of an Adaptive Cycle Aero-Engine |
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LI Bin1,2,CHEN Min1,ZHU Zhi-li1,ZHANG Kun1
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(1. School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;2. Shenyang Aeroengine Research Institute,Aviation Industry Corporation of China,Shenyang 110015,China)
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| Abstract: |
| A configuration of an Adaptive Cycle Engine (ACE) and the mechanism of its variable geometries were presented. An ACE simulation program was developed and utilized to analyze the matching principle and performance of various modes of ACE at typical operation points. Results show that throttle ratio is a critical design parameter influencing not only the engine thrust ratio at take-off but also the performance at high-altitude and high-speed missions. The utilization of variable Flade (Blade on Fan) makes it possible to fix the nozzle throat area when reheating the engine. Through the combined modulation of various variable geometries, more cycle modes are available and the variation of bypass ratio is greater(from 0.28to 1.43at take-off). Given the same thrust level, the specific fuel consumption of triple-bypass mode is less than the one of single-bypass mode, around 9.1% during subsonic cruise(H=11km,Ma=0.9) and 2.3% during supersonic cruise(Ma=1.5),respectively. |
| Key words: Adaptive cycle engine Simulation Thrust-weight ratio Throttle ratio Performance. |
