Aerodynamic Analysis of Rotor/Stator Interaction Based on Immersed Boundary Method

摘要

A fast explicit numerical scheme for solving unsteady, viscous, incompressible flow on a quasi-three-dimensional coordinate system is established for investigating the interaction between rotor/stator in turbomachinery. In the present scheme, because the governing equations are discretized on simple Cartesian meshes using immersed boundary method (IB method), the computational domain is not necessary to be subdivided into zones, which makes it flexible and fast for moving boundary and complex-topology problems. The numerical errors caused by the interface between blade rows are removed in the present scheme. The effects of varying the axial gap between adjacent blade rows are studied by simulating flow through a 7:6 rotor/stator system.