The aerodynamic performance of turbomachines is limited by flutter, choking, and stall, the last of whichbeing a topic of this report. Viscous flow considerations are not only essential in determining loss coefficients,but also in ascertaining loadings and in providing a fundamental understanding of the flow. However, becauseof the complexity' of flows in turbomachines flow problems of model character only are accessible to uumericaltreatment. The focus of this report is on steady, incompressible, viscous. 2-d flows through a single infinite row of equidistant blades. In order to compute these cascade flows Prandtl's boundary layer concept enhancedby a strong interaction model is applied to the Navier-Stokes equations. Since this approach enables theintegration of boundary layer equations in the presence of backflow. it is an attractive alternative to muchmore expensive Navier-Stokes solvers...
展开▼
