An Improved Mixing-Plane Method for Analyzing Steady Flow Through Multiple-Blade-Row Turbomachines

摘要

Presented in this paper is an improved method for dealing with a mixing plane that exists between computational domains of two adjacent blade rows of a multiple-blade-row tur-bomachine. The method makes use of the semidiscrete flow equation updating scheme to convert flux differences across an interrow interface to conservative flow variable incre-mentals then to characteristic variable perturbations. Therefore, the proposed method bears more physics and is much more robust than any known method of its kind. As a result, reverse flow can be accommodated by this method naturally without any special treatment. Two existing methods are also included to provide a clear illustration of the differences and advantages of the new method. Two numerical test cases using a transonic compressor stage are presented to investigate the robustness of the new method and its influence on solution convergence, accuracy, and time cost in comparison with the two existing methods.