A study on the three-dimensional flow calculation with viscous loss for the rotating blades in axial-flow compressors

A Numerical Calculation has been performed for the analysis of three-dimensional flow fields in the rotating cascade. This analysis is one of the most important part of the aerodynamic design of rotating blades in axial-flow compressors. Three-dimensional flow fields can be obtained by the quasi-three-dimensional iterative calculations of flows both on blade-to-blade stream surfaces and hub-to-shroud stream surfaces, the former is solved by the method of boundary streamline correction, the latter with the consideration of viscous flow losses. Conclusions are obtained as follows: 1) The method of boundary streamline correction has beeen proved to be accurate one for the calculation of the high subsonic compressible blade-to-blade flows. 2) For the prediction of performance at off-design points, the results of calculation of hub-to-shroud are effective if the calculation is performed with the proper consideration of losses due to viscous flows. (Author)