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跨音压气机/风扇旋转失速稳定性模型
引用本文:于巍巍,孙晓峰. 跨音压气机/风扇旋转失速稳定性模型[J]. 航空动力学报, 2005, 20(6): 1018-1027
作者姓名:于巍巍  孙晓峰
作者单位:北京航空航天大学能源与动力工程学院,北京100083
基金项目: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。 

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
文章编号:1000-8055(2005)06-01018-010
收稿时间:2005-06-26
修稿时间:2005-06-26

Rotating Stall Stability Theory of the Transonic Axial Compressors/Fans
YU Wei-wei and SUN Xiao-feng. Rotating Stall Stability Theory of the Transonic Axial Compressors/Fans[J]. Journal of Aerospace Power, 2005, 20(6): 1018-1027
Authors:YU Wei-wei and SUN Xiao-feng
Affiliation:School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract: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.
Keywords:aerospace propulsion system  rotating stall  shock wave  stability model  winding number integral method
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