摘要
针对短距起飞垂直降落型(STOVL)战斗机的发动机特性进行分析。在常规双轴涡扇发动机性能模拟程序的基础上,添加了升力风扇与滚转控制喷管部件模块,并加入了尾喷管喉道面积、模式选择阀门面积和低压涡轮导向器面积等调节变量,编写了带升力风扇的变循环发动机整机性能数值模拟程序,选取超音速巡航状态设计点,确定设计点各参数,计算分析了带升力风扇的STOVL型变循环发动机在超音速巡航状态、海平面静止状态及STOVL状态的性能参数。研究结果表明:这种创新的变循环推进系统,通过改变发动机有效涵道比,提供了较大的推力增加,同时降低了耗油率。
The aim of this paper is the description of the performance characteristics of a powerplant intended for modern STOVL fighters.Based on a general two-shaft gas turbine performance simulation software,a variable cycle engine performance simulation software was developed with introduction of Lift fan and Roll posts modules.The cycle operating parameters were given,such as low pressure turbine nozzle area,mode selector valve area and propelling nozzle throat area.Selected supersonic cruise as designed point of the engine,determined the combination of the parameters which forming the design point of the engine.The performance characteristics of variable cycle engine with a low pressure shaft driven lift fan were calculated and analyzed on supersonic cruise Design Point,SLS and STOVL in this paper.Comparing the parameter values of SLS and STOVL points,it is actually verified that the innovative variable cycle propulsion system offers high levels of thrust augmentation,by altering the effective engine bypass ratio,offering simultaneously improved fuel consumption.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2011年第6期13-17,共5页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国家自然科学基金资助项目(51106179)
空军工程大学研究生创新基金资助项目(DX2010104)
关键词
变循环发动机
短距起飞垂直降落
发动机性能
数值模拟
variable cycle engine
Short Take Off and Vertical Landing（STOVL）
engine performance
numerical simulation
