短距起飞/垂直降落发动机建模技术研究  

Research of short take off and vertical landing engine modeling techniques

作　　者：任冰涛[1] 李秋红[1] 亢岚[2] 王元[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]内蒙古科技大学矿业与煤炭学院,内蒙古包头014010

出　　处：《航空动力学报》2015年第10期2531-2538,共8页Journal of Aerospace Power

基　　金：航空科学基金(20110652003);江苏省优势学科资助

摘　　要：参考常规双轴涡扇发动机数学模型,建立了适用于短距起飞/垂直降落(STOVL)飞机的变循环发动机部件级数学模型;通过特性外推,建立了轴驱动升力风扇数学模型;采用神经网络映射涵道总压损失的方法,建立了滚转喷管和外涵模型.根据STOVL发动机结构和部件变化特点,建立了稳态和动态共同工作方程.参照国外文献仿真数据进行设计点计算,并按照Bevilaqua提出方法开展了由常规涡轮风扇模式到悬停涡轮轴模式的过渡态仿真.仿真结果表明:建立的数学模型在悬停状态设计点和高空巡航点与国外文献数据相比误差均小于1.5%,推力达到悬停状态要求,符合STOVL发动机的设计特点,验证了该建模方法的有效性.The component-level model of variable cycle engine for short take off and ver- tical landing （STOVL） was built based on modeling method of two-spool-turbofan engine. On the basis of characteristics extrapolation method, the shaft-driven lift fan mathematical model was built. Models of the bypass duct were built using neural network for mapping the bypass total pressure loss. According to the structure and specialty of short takeoff and ver- tical landing, the static and dynamic co-working equations were set up. With reference to foreign researches＇ simulation data, the design point was calculated. According to Bevilaqua＇s method, transient simulation of switching between conventional turbofan and hover turboshaft cycle was carried out. The results of numerical simulation indicate that the error of the mathematical model and foreign research data is less than 1.5%, and the thrust meets hover state requirements. Both models can offer high levels of thrust by increasing the fuel flow a little. The performance variation in simulation is consistent with the specialty of STOVL, so the modeling method of STOVL proposed is feasible.

关 键 词：短距起飞/垂直降落(STOVL) 升力风扇 过渡态仿真 变循环发动机 建模技术 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]