The use of 3D steady and unsteady CFD methods in modelling the aerothermodynamics of turbine blades is presented. Models are presented for the steady flow in a high pressure turbine rotor with and without the effects of the flow over the rotor shroud; the pseudo-steady interaction effects in a turbine stage through a steady multi-stage analysis; and, the 3D time dependent rotor/stator interaction effects through an unsteady analysis. Models are also presented for the cooling mechanisms used in modern gas turbines and include features such as film cooling and trailing edge ejection.
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