摘要
对于混合排气加力涡扇发动机可变几何参数调节对其性能的影响进行了分析研究，结果表明在超声速飞行条件下调节几何参数对于改善性能有显著效果。
The impact of variable geometry adjustment on performance of military turbofan engine with afterburner is analyzed and discussed.The results show as follows:During supersonic flight,increasing the nozzle throat area is an effective way to increase thrust of engine,and the higher the flight Mach number,the more remarkable the effectiveness;the nozzle throat area enlargement results in raising the surge margin of the fan effectively;the bypass ratio can be controlled by adjusting the ratio of inner and outer areas at mixer inlet,and enlarging inner area improves the performance of the engine with afterburner,but narrows the surge margin of the fan.The operating point of the fan will be optimized when the nozzle throat area and the area ratio of mixer inlet are regulated jointly and coordinately.It will be of benefit to the engine performance improvement that the pressure ratio of the fan and the mass flow increase simultaneously,while the efficiency and the surge margin of fan are kept up at a high level.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1994年第4期353-356,共4页
Journal of Aerospace Power
关键词
燃气轮机
涡扇发动机
性能分析
可变几何
Gas turbines Aircraft engines Performance analysis Variable geometry adjustment
