变循环发动机模态转换的几何调节规律  

Geometry regulating law of variable cycle engine during mode transition

作　　者：周红[1] 王占学[1] 张晓博[1] 张明阳[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2015年第9期2160-2166,共7页Journal of Aerospace Power

摘　　要：考虑了变循环发动机转子惯性效应和部件容积效应,分析了模态选择阀门面积、核心驱动风扇级导叶角度、低压涡轮导向器面积、喷管喉部面积等几何参数及其不同组合调节方式对变循环发动机模态转换过程的影响,并与实验数据进行了对比.结果表明:所建立的数学模型能正确反映变循环发动机在模态转换过程中参数的变化规律.为确保转换过程的顺利进行,在放大(关小)模态选择阀门面积时,应关小(放大)核心驱动风扇级导叶角度.低压涡轮导向器面积和喷管喉部面积的调节可使得转换过程中参数的变化更加平稳.The inertial rotor dynamics and volume dynamics of variable cycle engine were considered.The influences of mode selector valve area,core driven fan stage inlet guide vane,low pressure turbine area,nozzle throat area and their different combined adjustments on variable cycle engine mode transition performance were analyzed and compared with the test data.The results indicate that the simulation model established can calculate the characteristic of variable cycle engine mode transition correctly.It is suggested that the core driven fan stage inlet guide vane should been closed/opened when the mode selector valve area is opened/closed during mode transition.The parameters can change more smoothly by adding reasonable regulation of low pressure turbine area and nozzle throat area.

关 键 词：变循环发动机 模态转换 几何调节规律 模态选择阀门 核心驱动风扇级导叶角度 

分 类 号：V235.16[航空宇航科学与技术—航空宇航推进理论与工程] TP301.6[自动化与计算机技术—计算机系统结构]