Abstract
Grid generation technique and boundary conditions are studied to calculate accurately the flow fields for supersonic turbine cascades which have a low solidity and a high stagger angle. A structured multi-block structure is used with an offset periodic grid around a blade to reduce skewness of the grid for highly staggered blades. Nonreflecting boundary conditions based on two-dimensional characteristic theory proposed by Giles are applied for supersonic inflow and outflow to avoid spurious nonphysical reflections of shock waves at the boundaries. The effectiveness is confirmed for a supersonic aerofoil of a moving blade of the last stage of steam turbine.
