中文摘要：

基于部件匹配和多设计点分析技术,发展了加装升力风扇的涡扇发动机性能计算模型.以F135涡扇发动机为例,对模型的可靠性进行了验证.数值模拟结果表明：升力风扇不工作时,涡扇发动机性能模拟与常规涡扇发动机是一致的,当升力风扇工作时,若实现低压涡轮与涡扇发动机风扇、升力风扇工作点的匹配,不仅需要调节尾喷管喉道面积,而且可变外涵道出口面积、低压涡轮导向器喉部面积也需要调节.基于该模型,可以进行带升力风扇的涡扇发动机循环参数匹配和不同任务状态的性能分析.

英文摘要：

Based on component matching and multi-point analysis,a turbofan plus lift fan engine performance simulation model was developed.The model was tested by the F135 engine.The simulation results show that the engine performance is the same as the conventional turbofan in cruise mode.When the lift fan is engaged,the matching point between the low pressure turbine,the cruise fan and the lift fan is achieved by adjusting the nozzle throat area,the bypass exit area,and the low pressure turbine throat area.Based on this model,the cycle parameter matching and performance analysis can be achieved for the turbofan plus lift fan engine in different missions.