风扇/增压级内外涵联算的特性数值模拟  

Performance numerical investigation of double-channel fan/compressor

作　　者：李晓娟[1] 金海良[1] 桂幸民[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机数值仿真研究中心,北京100191

出　　处：《航空动力学报》2009年第12期2719-2726,共8页Journal of Aerospace Power

摘　　要：提出了一种风扇/增压级内外涵联算的多转速全工况快速特性预测的计算方法.该方法将模化的叶片法向力和摩擦力引入周向平均形式的Euler方程组源项,结合NASA SP-36提供的攻角和落后角确定方法以及Koch稳定边界模型,对高负荷跨声风扇级以及某双涵道大涵道比的风扇/增压级进行了特性数值模拟,并与实验和三维数值模拟结果进行了比较.结果显示周向平均方法基本满足风扇/增压级初期气动设计快速特性预估的工程精度要求.A core and bypass combined calculation method of full-speed performance and surge boundary of the multi-stage double-channel fan/compressor was established.The circumferentially averaged Euler equations with two modeling source terms were employed to reduce the overall computation effort,while modeling blade force and friction force were employed along with incidence angle and deviation angle proposed by NASA SP-36 to model the two source terms.By combining with Koch surge boundary model,the simulation prog...

关 键 词：风扇/增压级 全工况特性预测 内外涵联算 数值模拟 气动设计 

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]