The performance of a transonic axial turbine stage, representative of a wide class of aeroengines, is computed by a Navier-Stokes solver with a three-equation turbulence model. The stator blade has a coolant ejection slot on the pressure side close to the trailing edge. The stator-rotor interaction is modelled by a mixing plane approach. The tangential mixing strategy is discussed and analysed in terms of area or mass averaging. The computational results are compared with an experimental data set, which includes all the relevant quantities necessary to describe the stage. Both computations and experiments are carried out in four different operating conditions to allow first the effects of changes in Reynolds number and pressure ratio to be assessed and second the sensitivity of the computational model to these changes to be tested. The effect of tip leakage is investigated and CFD is used to help understand the experiments. The predictions compare favourably with experiments for most of the relevant parameters and prove the validity of the simple and fast computational model.

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