A procedure is presented for automated and fast geometry/grid generation of threedimensional, multi-stage, axial turbomachinery for multi-disciplinary simulations involving fluid/thermal, fluid/structural, or fluid/thermal/structural interaction. The procedure generates geometry for solid airfoils and endwalls, thermal barrier coatings, heat transfer pedestals, cooling plenums, cooling/flow-control tubes, and inter-blade-row endwall leakage slots as well as the computational grids for these components. The computational grids that are generated in general consist of multi-block, point-matched structured grids. For the cooling/flow-control tubes, heat transfer pedestals, and inter-blade-row leakage slots, the computational grids are embedded, multi-block, overset grids to allow for arbitrary placement to allow optimization without the need for re-gridding the entire domain. The techniques used to construct the geometry and various computational grids are described. Demonstration of the procedure is provided for a 1½ stage film-cooled turbine and a single stage compressor.