Abstract
A procedure is presented for automated and fast geometry-grid generation of three-dimensional, multistage, axial turbomachinery for multidisciplinary simulations involving fluid–thermal, fluid–structural, or fluid–thermal–structural interaction. The procedure rapidly generates geometry for solid airfoils and endwalls, thermal barrier coatings, heat transfer pedestals, cooling plenums, cooling flow control tubes, and interblade row endwall leakage slots as well as the computational grids for these components automatically based on prescribed input parameters. The computational grids that are generated in general consist of multiblock, point-matched structured grids. For the cooling flow control tubes, heat transfer pedestals, and interblade row leakage slots, the computational grids are embedded, multiblock, overset grids to allow for arbitrary placement to allow optimization without the need for regridding the entire domain. The techniques used to construct the geometry and various computational grids are described. Demonstration of the procedure is provided for a one-and-a-half stage film-cooled turbine and a single-stage compressor. The geometry parameterization, as well as the automated geometry and grid topology construction, makes this a unique and rapid approach for multidisciplinary grid generation of multistage turbomachinery configurations during design optimization.
Published Version
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