第四代战斗机推进系统循环参数优化研究

RESEARCH ON OPTIMIZATION OF CYCLE PARAMETERS FOR ATF PROPULSION

本文对有和没有超音速巡航任务段的第四代战斗机推进系统的循环参数进行了最优化计算，分析了超音速巡航距离、发动机全寿命费用和部件效率对发动机最优循环参数选取的影响。结果表明宜采用小涵道比涡扇发动机，而且不考虑费用时涡轮前温度取值越高越好，考虑费用时则有最大值；提高发动机部件效率对循环参数取值影响较大，而且使飞机性能提高较多。

The cycle parameters of ATF propulsion with or without supersonic cruise missions have been optimized respectively and compared.And the effects of supersonic cruise range,engine life cycle cost and engine part efficiencies on the optimization of the engine cycle parameters have been researched.The results show that a turbofan engine with a small bypass ratio must be installed,and a suitable turbine entry temperature is obtained by optimization with life cycle cost.The enhancement of the engine part efficiencies has influence on the optimization of the cycle and the aircraft markedly raises the aircraft performance.The afterburner temperature must be taken very high due to the limit of the engine maximum diameter.