风扇与轴流离心压气机一体化通流设计方法  

Integrative design method of fan and axial-centrifugal compressor

作　　者：杨小贺[1] 单鹏[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2010年第2期443-450,共8页Journal of Aerospace Power

基　　金：北京市教育委员会共建项目(XK100060420)

摘　　要：在叶轮机设计的流线曲率法反问题中,统一了基于圆柱坐标系下流面角γ,λ的和流线准法线上流面角的两种叶片力分解方法,得到了适合于轴流、斜流和离心压气机的动量主控方程.提出一种双涵道叶轮机的一体化通流反问题方法,采用分流机匣变位或者涵道比变化这两种自动调整措施.将流线曲率法应用于双涵道叶轮机加以组合压气机的一体化通流设计.设计了某双涵道、双转子、轴流离心组合的压缩系统,用计算流体动力学(CFD)方法检验了可行性和适应性.讨论了轴向速度比的物理意义及在通道自动调整的轴流级通流设计中的应用,给出相应设计算例.Firstly,for the S2,m streamline-curvature approach,the blade force decomposition method using two stream surface angles in the cylinder coordinates was associated with that using one stream surface angle of the computing station quasi-orthogonal to the streamline; then a control momentum equation suitable for axial-, radial- and mixed-flow type compressors was derived. Secondly,an integrative bypass-turbomaehine through-flow inverse design method was proposed, which employs either the convergence strategy of automatically re-positioning the splitter or that of re-calculating the bypass ratio. So an integrative design method for the compression system of fan added by an axial-centrifugal compressor was presented. This method has been applied to a two-channel two-shaft system consisting of a two-stage fan, two-stage booster and a centrifugal compressor. The flow fields of first fan stage and the centrifugal impeller were checked by computational fluid dynamics （CFD）,demonstrating the operational feasibility and flexibility of this method. Thirdly,the physical significance of the axial velocity ratio and its application in an axial-flowpath self-adjusting inverse problem were discussed. The simpleness and convenience of the axial velocity ratio as a design parameter are showed by another example.

关 键 词：叶轮机设计 流线曲率法 叶片力 双涵道叶轮机 组合压气机 轴向速度比 

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]