Rapid Meshing of Turbomachinery Rows Using Semi-Unstructured Conformal Grids

The aerodynamic design of uncooled turbomachinery rows is based, among other things, on the repeated simulation of three-dimensional blade rows with a fast turnaround time. Traditionally blade rows have been simulated using clean aerodynamic surfaces and simplified computational domains consisting of just the aerodynamic surface and an approximated main annulus. A more accurate and realistic representation of the flow geometry would require the inclusion of the tip-shroud and under platform cavities, the airfoil platforms themselves and the sealing flows, which on the other hand have been shown to have a large influence on the development of