低压涡轮导向器开度对变循环发动机的影响  

Influence of Low Pressure Turbine Guide Opening on Variable Cycle Engine

作　　者：何雨婷 王英锋[1] HE Yuting;WANG Yingfeng(College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2023年第4期651-657,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：建立了变循环发动机整机模型并对可变几何低压涡轮特性进行修正,研究了低压涡轮导叶开度从-6°~6°时对各部件以及发动机整体性能的影响。结果表明:随低压涡轮导向器角度变大,低压涡轮进口折合流量增大,不论低压涡轮导向器开大或关小,高、低涡轮效率均下降;随导叶开度增大,高压涡轮膨胀比增大,高压轴功率增大,高压压气机(High pressure compressor,HPC)与核心机驱动风扇级(Core driven fan stage,CDFS)压比增大;双外涵模式下涡轮导叶角度为0°时单位推力最大,单外涵模式下涡轮角度为-1°时单位推力最大。The variable cycle engine model is established and the variable geometry low pressure turbine characteristics are modified.The results show that the reduced flow rate at the inlet of the low pressure turbine increases with the increase of the angle of the low pressure turbine deflector.With the increase of guide vane opening,the expansion ratio of high pressure(HP)turbine,the power of HP shaft,and the pressure ratio of high pressure compressor(HPC)to core driven fan stage(CDFS)increase.The specific thrust reaches its maximum when the turbine guide vane angle is 0°in double bypass mode and the turbine angle is-1°in single bypass mode,respectively.

关 键 词：变循环发动机 变几何低压涡轮 导叶开度 涡轮效率 单位推力 单位耗油率 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]