摘要
基于多级轴流压气机的逐级特性，建立了一种预估多级轴流压气机在均匀进气和周向压力畸变进气条件下的喘振边界的新方法，基于动态压缩系统模型，对8级轴流压气机喘振边界进行了数值预测。结果表明，新方法不仅能较准确地预估多级轴流压气机的喘振边界，而且还能同时给出不稳定临界级。通过数值结果与实验结果的比较，表明了新方法的有效性。
A new method for simulating surge line in multistage axial compussors with clean orpressue distortion inlet flow has been established based on stage-by-stage compressor characteristics.The nonlinear conservative equations are solved using second-order accurate MacCormack finitedifference scheme. The numerical sesults for an eight-stage axial compressor show that this method isable to predict surge time in multistage axial compussors correctly,and also to give critical instabilitystage. It is apparent that the numerical simulation with authors'method gives results in goodagreement with experimental data. Finally,a parameter of recognition of aerodynamic stability is alsofound.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第2期75-77,共3页
Journal of Propulsion Technology
基金
航空科学基金
关键词
轴流式压气机
喘振
气动稳定性
航空
Axial flow compressor, Surge, Aerodynamic stability, Mathematical prediction
