The aero-thermal performance of highly loaded High-Pressure turbines is abated by the unsteady impact of the vane shocks on the rotor. This paper presents a detailed physical analysis of the stator-rotor interaction in a state-of-the-art transonic turbine stage at three pressure ratios. The experimental characterization of the steady and unsteady flow field was performed in a compression tube test rig. The calculations were performed using the ONERA's code elsA. This original comparison leads to an improved understanding of the complex unsteady flow physics of a HP turbine stage. The vane shock impingement on the rotor originates a separation bubble on the rotor crown that is responsible of the generation of large pressure losses. A simple model is proposed to predict this pressure loss. Furthermore the unsteady forcing is analyzed in detail.
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