摘要
在常规双轴涡扇发动机性能模拟程序的基础上,添加了模式选择阀门、前可调面积涵道引射器、后可调面积涵道引射器、核心涵道等部件模块,并加入了低压涡轮导向器面积、高压压气机转子叶片角度、风扇转子叶片角度、核心驱动风扇级转子叶片角度等调节变量,编写了双外涵变循环发动机性能数值模拟程序,模拟了一种带核心风扇级的双外涵变循环发动机的高度、速度和节流特性.计算表明:与单外涵模式相比,双外涵模式的单位推力和耗油率低,受飞行条件影响的主要为前涵道比.随着低压转子转速的降低,双外涵模式的总涵道比呈增大的趋势,发动机的耗油率大幅降低.此外,变循环发动机在几何调节参数不变的情况下,对工作条件较敏感,必须特别注意各调节参数与发动机工作条件的匹配.
Based on a general gas turbine performance simulation software,a double bypass VCE（variable cycle engine） performance simulation software was developed with introduction of selector valve,forward VABI（variable area bypass injector） and rear VABI and core bypass duct modules.The cycle operating parameters of VCE were given,such as low pressure turbine nozzle area,compressor inlet guide vane angle,fan inlet guide vane angle and core-driven fan stage inlet guide vane angle.A double bypass VCE characteristics were calculated and analyzed with altitude velocity and throttling in this paper.Compared with single bypass mode,the specific thrust and specific fuel consumption（SFC） of double bypass mode were low.The total bypass ratio increased and the SFC decreased with the decline of rotate speed.Under a complicated condition,it is necessary to match the engine with appropriate variable parameters.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第6期1310-1315,共6页
Journal of Aerospace Power
关键词
变循环发动机
双外涵
核心风扇级
数值模拟
性能特性
variable cycle engines
double bypass
core-driven fan stage
numerical simulation
performance
