Abstract
A methodology is introduced for generating three-dimensional hybrid meshes for turbomachinery airfoils. This method creates a volume mesh by stacking layers of area meshes along the blade spanwise direction. The area meshes are hybrid meshes composed of a structured O grid around the airfoil and an unstructured grid in the rest of the domain. Each layer ofthe stacked mesh is mapped from a single source mesh. Optimization-based smoothing is applied to the mapped area mesh to increase mesh quality. The optimization-based smoothing is also applied to the periodic boundaries to optimize the placement of the grid points. Further enhancement of grid quality is obtained by edge swapping and node insertion. Edge swapping reduces the dependency of mesh quality on the choice of the source mesh. The meshing algorithm is tested on a challenging turbine rotor airfoil whose stagger angle varies approximately 88 deg from hub to tip.
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