周向稳态总压畸变在多级轴流压气机中传递的逐级模拟研究  

Study of staged propagation of circumferential steady total pressure distortion in axial flow compressors

作　　者：芮长胜[1] 吴虎[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2007年第12期2031-2035,共5页Journal of Aerospace Power

基　　金：国家自然科学基金(10377013);航空科学基金(02C53022)资助课题

摘　　要：基于多级轴流压气机的逐级特性,建立了进口周向稳态总压畸变在多级轴流压气机中传递的逐级计算模型.对总压畸变条件下转子叶片攻角变化、级间周向流动和压气机出口耦合效应进行了数值分析,讨论了周向稳态总压畸变沿轴向衰减、级间周向侧流变化、失稳首发级和压气机出口耦合效应对压气机特性的影响.应用本模型方法对8级轴流压气机进行了详细的数值分析,计算结果表明,该模型方法是合理、可行的.Based on the stage characteristics of axial flow compressor, a new model was established for calculating the propagation of circumferential steady total pressure distortion in multistage axial flow compressors. The inlet angle of attack, circumferential flow of sta- ges and coupled compressor diffuser flow were also analyzed numerically. Meanwhile, the in- fluences of axial attenuation of circumferential steady total pressure distortion, unsteady primary level and coupling performance of compressor outlet on the characteristic of compressor were discussed. Based on this model, the multistage axial flow compressors were analyzed numerically, proving that this model is reasonable and feasible.

关 键 词：航空 航天推进系统 总压畸变 轴流压气机 传递 周向侧流 失稳 

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]