摘要
为了改善增压级流场特性、提升包括增压级在内的低压压气机部件的性能水平,本文开展了增压级末级流路和末级静叶安装角的优化设计。通过优化增压级末级动叶和静叶的进口马赫数,验证了末级流路大曲率变化特征对于叶片根部流场的影响;通过优化末级静叶的安装角,降低了内涵支板对上游流场的堵塞效应;在此基础上,实现了低压压气机部件性能水平的提升。三维数值求解结果表明,低压压气机部件设计工况的效率提升了0.30个百分点;末级静叶进口静压的最大值下降了约2000 Pa,进口静压的周向不均匀性明显降低。本文的研究成果在大涵道比航空发动机压缩部件的气动设计中具有重要的工程应用价值。
To improve the flow field of booster and characteristics of low pressure compressor,numerical calculation is carried on to optimize the last stage path and the last stator stagger angle.By analyzing and optimizing the inlet Ma of the last stage rotor and stator respectively,the effect of sharp curvature variation on flowing characteristics was verified in the last stage.By optimizing the stagger angle of the last stator,the strut blockage effect on the upstream flow was reduced.Furthermore,performance of the low pressure compressor was enhanc ed significantly.Efficiency was raised with 0.30%,the maximum static pressure was decreased with about 2000 Pa at the inlet of the last stator.It is eventful to guide the compressor aero design of the high bypass ratio aero engine.
作者
裴小萌
刘佳骏
杨小贺
Pei Xiaomeng;Liu Jiajun;Yang Xiaohe(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China)
出处
《燃气轮机技术》
2019年第4期15-22,33,共9页
Gas Turbine Technology
关键词
增压级
数值模拟
流路
马赫数
安装角
booster
numerical simulation
flowpath
Mach number
stagger angle
