Abstract
A procedure is presented for the parallel, steady and unsteady conjugate, NavierStokes/heat-conduction rotor-stator interaction analysis of multi-blade-row, film-cooled, turbine airfoil sections. A new grid generation procedure for multiple blade-row configurations including walls, thermal barrier coatings, plenums, and cooling tubes is discussed. Steady, multi-blade-row interaction effects on the flow and wall thermal fields are predicted using a Reynolds’s-averaged Navier-Stokes simulation in conjunction with an inter-blade-row mixing plane. Unsteady, aero-thermal interaction solutions are determined using time-accurate sliding grids between the stator and rotor with an unsteady Reynold’saveraged Navier-Stokes model. Non-reflecting boundary condition treatments are utilized in both steady and unsteady approaches at all inlet, exit, and inter-blade-row boundaries. Parallelization techniques are discussed. Demonstration of the procedure is provided for a transonic turbine stage.
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