周向总压畸变对多级轴流压气机稳定性影响的逐级模拟方法  

Stage-by-Stage Simulation Method of Circumferential Total Pressure Distortion Effect on Multistage Axial Flow Compressor Stability

作　　者：芮长胜[1] 吴虎[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《航空发动机》2007年第3期11-14,共4页Aeroengine

基　　金：航空科学基金(02C53022)

摘　　要：介绍了1种分析进口总压畸变对多级轴流压气机特性影响的逐级模拟方法。应用该方法对J85-13压气机的进口总压畸变进行了分析,并对压气机在稳态和畸变情况下特性的逐级模拟计算结果进行了详细的数值分析,讨论了压气机的失稳关键级以及有效进气攻角对多级轴流压气机特性的影响。计算结果与试验结果的比较表明,该模拟方法是合理可行的。A stage - by - stage simulation method is introduced for analysis of inlet total pressure distortion effect on the multistage axial flow compressor characteristics. The detail simulation of inlet total pressure distortion is conducted by this method for J85 - 13 compressor, the effect of critical stage for instability and effective incidence on multistage axial flow compressor characteristics is discussed. The simulations are compared with the available test data. The results show that the method is advisable.

关 键 词：总压畸变 轴流压气机 气动稳定性 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]