CAJ | 학술논문

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。
기우다급축류압기궤적축급특성，건립료일충예고다급축류압기궤재균균진기화주향기변진기조건하적천진변계적일유수치모의방법。근거동태압축계통모형，대일태량급풍선적천진변계진행료수치예측，여기우리아보낙부이론적선화일유모형화시험결과적비교표명，해모형능교위준학지예고다급축류압기궤적천진변계。대기변진기조건하량급풍선은정성진행적상세수치분석표명：진기총압기변재류동과정중회생성총온기변병반수착총압기변적쇠감，진기총온기변칙회생성총압기변병반수착총온기변적쇠감；반향총온총압조합기변진기시，기변쇠감쾌은정유도손실소，이정향총온총압조합기변진기시，기변쇠감만은정유도손실대。
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.