Abstract
The present research concerns the aerodynamic computational studies of stator-rotor turbine stage. The computational studies are carried out using the large-eddy simulation approach. In the aircraft engine compressor/turbine stage blade-vortex interactions occur. The present study aims at the understanding the blade-vortex interaction mechanism and its impact on the aerodynamics of rotor-stator compressor/turbine stages. The computational studies are carried out in a rotating frame of reference, for high-Reynolds number flow, Re = 1.3x105. The analysis reveals that the blade-vortex interaction causes the flow separation on the stator stage and a time-varying lift and drag.
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