跨音压气机/风扇旋转失速稳定性模型  

Rotating Stall Stability Theory of the Transonic Axial Compressors/Fans

作　　者：于巍巍[1] 孙晓峰[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2005年第6期1018-1027,共10页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50136010)

摘　　要：以一个三维可压缩旋转失速稳定性模型为出发点,通过引入带有激波的半激盘模型建立了针对跨音压气机/风扇的稳定性模型,并通过与一些实验结果的对比验证了模型的有效性。另外,环绕积分求复函数根方法尽管早已存在,但是却不被广泛使用,该方法实际上比N ew ton-R aphson方法具有更稳定和高效的特点,该方法在跨音模型上的成功应用证明了该方法值得推广。One semi-actuator stability model for rotating stall considering in-passage shock wave was developed based on a three-dimensional compressible theory,and it was evaluated to be effective by comparing the results with experiments. Winding number integral method has been developed to solve the roots of complex functions for a long time,although it is not widely used, in some way,it is more stable than Newton-Raphson iteration method. The author used this approach to solve the eigen equation of the transonic stability model, and it is strongly recommended to extend its use in other fields because of its advantages over other methods.

关 键 词：航空、航天推进系统 旋转失速 激波 稳定性模型 环绕积分法 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]