Shock-wave/boundary-layer interaction in a transonic turbine cascade

摘要

Shock-wave/boundary-layer interaction (SWBLI) in a transonic turbine cascade was researched numerically using large eddy simulation (LES) and the results were compared with experimental data to verify the method. The investigation indicated that, the LES reproduced the SWBLI process accurately. The flow details in the SWBLI region appeared highly three-dimensional characteristic. The contours of span-wise vorticity on suction surface in the separation bubble were presented to indicate the transient flow development. The surface limiting streamlines turned out to be two counter-rotating vortices. The SWBLI caused a pressure fluctuation on the suction side downstream of this region. The maximum value was about 2 per cent of the local mean pressure.