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畸变进气条件下的喘振边界的一维数值模拟方法。根据动态压缩系统模型,对一台两级风扇的喘振边界进行了数值预测,与基于李亚普诺夫理论的线化一维模型和试验结果的比较表明,该模型能较为准确地预估多级轴流压气机的喘振边界。对畸变进气条件下两级风扇稳定性进行的详细数值分析表明:进气总压畸变在流动过程中会生成总温畸变并伴随着总压畸变的衰减,进气总温畸变则会生成总压畸变并伴随着总温畸变的衰减;反向总温总压组合畸变进气时,畸变衰减快稳定裕度损失小,而正向总温总压组合畸变进气时,畸变衰减慢稳定裕度损失大。
A quasi one-dimensional, stage-by-stage axial compression system mathematical model for sim-ulating surge line with clean or distortion inlet flow has been constructed based on compressor stage charac-teristics. The surge margin of a two stage fan was predicted by simulation according to the dynamic compres-sion system model. Compared with the experimental data and the linear model based on Liapunov’s theory, it is apparent that this model can predict the axial flow compressor’s stability margin correctly. According to the detailed numerical results for the stability of the two stage fan, inlet total pressure distortion will lead to the generation of total temperature distortion and decrease in the flowage, inlet total temperature distor-tion will cause total pressure distortion generation and reduce at the same time. Further more, inlet oppos-ing combined distortion of pressure and temperature cause drastic distortion decrease and moderate stabili-ty margin loss, while inlet overlaped combined distortion of pressure and temperature cause comparatively moderate distortion decrease and drastic stability margin loss.
出处
《燃气涡轮试验与研究》
北大核心
2014年第4期1-6,共6页
Gas Turbine Experiment and Research
关键词
航空发动机
轴流压气机
一维模型
畸变
气动稳定性
数值模拟
aero-engine
axial flow compressor
stage-by-stage model
distortion
aerodynamic stability
numerical simulation
