摘要
建立了预测畸变进气压气机特性与气动稳定性的改进多子区平行压气机模型。为了检验该模型的准确性，进行了均匀及１８０°畸变进气下单级压气机特性与气动稳定性的实验研究。以实测的均匀进气单级压气机特性为基础，应用改进的多子区平行压气机模型，在与进气畸变实验完全相同的条件下，对畸变进气单级压气机等转速线及其不稳定工作点进行了预测，预测与实验吻合良好，证明该模型是有效的。
An improved multiple segment parallel co mpressor model has been established to a nalyze the effect of steady state circum ferential total pressure distortion on c ompressor characteristics and aerodynami c stability.The distortion induced inlet flow redistribution,unsteady flow accel eration effects,unsteady rotor loss effe cts are considered.In order to verify th is model,the characteristics of a single stage axial flow compressor with unifor m inlet and 180° distorted inlet,as well as its aerodynamic stability were inves tigated experimentally.Under the same co nditions as in experiments,the effect of 180° intake flow distortion on the sing le stage axial flow compressor performan ce and aerodynamic stability was predict ed by the improved multiple segment para llel compressor model.The good agreement of the model prediction with the test d ata shows that the improved multiple seg ment parallel compressor model is valid for analysis of the effect of intake flo w distortion on compressor characteristi cs and aerodynamic stability.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1995年第1期87-89,共3页
Journal of Aerospace Power
基金
航空科学基金
关键词
进气道畸变
压气机
气动稳定性
航空发动机
Inlet disto rtion Parallel compressor theory Compres sor characteristics
