摘要
本文重点介绍采用二维可压缩非定常的 Euler方程描述回转面上无叶区的流动 ,并利用二维可压缩“激盘”取代压气机的转子和静子叶排 ,分析进气周向畸变对轴流压气机性能影响的模型。该模型中各叶排的损失和转折角直接由与均匀进气子系统完全相同的方法计算确定 ,从而克服了在解决此类问题时通常需要给定各叶排损失和转角特性的困难。本文还重点分析了进口周向总压畸变经过 RB-1 99高压压气机的衰减和对该压气机性能的影响 ,并分析了气动负荷的影响。
A model is proposed to analyze the influence of inlet circumferential distortion on axial flow compressor off design performance.The model describes the flow fields in blade free sections using two dimensional,compressible unsteady Euler equations,and replaces each blade row of the multistage compressor with a compressible “actuator disk”.The axisymmetric characteristics of each blade row in the model is directly calculated with the help of same method as in the subsystem with uniform inlet flow.Thus there is no difficulty in the model to give the characteristics of each blade row of the compressor calculated.Attenuation of an inlet circumferential total pressure distortion through a five stage high speed compressor and it's influence on the compressor performance are analyzed in detail.The comparison of the analyzed results with the available experimental data demonstrates that the model is reliable.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2000年第3期229-232,共4页
Journal of Aerospace Power
关键词
压气机
气动特性
物理模型
周向畸变
compressor
aerodynamic characteristics
physical models
