Evaluation of a numerical calculation method for unsteady flow in turbomachinery

The real blade-to-blade passage geometry can be computed owing to approximate treatment of the flow continuity condition on periodic boundaries.This technique is specifically intended to reduce the computational domain.The boundary treatment induces some approximate computation of the unsteady flow phenomena.These were analyzed in the cases of the E3 high-pressure turbine in which the viscous flow was computed.The main conclusion is that,this approach doesn't affect the time average performance parameters and can also be applied to multi-stage turbines.