Unsteadiness of shock-boundary layer interactions in a Mach 2.0 supersonic turbine cascade
نویسندگان
چکیده
The physics of shock-boundary layer interactions (SBLIs) in a supersonic turbine cascade at Mach 2.0 and Reynolds number 395,000, based on the axial chord, is investigated through wall-resolved large eddy simulation. Special attention given to characterization low-frequency dynamics separation bubbles using flow visualization, spectral analysis, space-time cross correlations, modal decomposition. mean flowfield shows different shock structures formed both sides airfoil. On suction side, an oblique impinges turbulent boundary layer, whereas reflection interacts with pressure side layer. taking place present show similarities discrepancies respect more canonical cases. For example, characteristic frequencies shock/bubble motions are comparable those described literature However, bubble leads compression waves that do not coalesce into shock, thin forms despite strong normal from reflection. Instantaneous visualizations illustrate elongated streamwise incoming layers their shocks bubbles. cross-correlations reveal near-wall streaks drive motion bubble, which turn promotes oscillations reattachment shear flapping. Organized SBLIs corresponding spatial support identified proper orthogonal
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ژورنال
عنوان ژورنال: Physical review fluids
سال: 2022
ISSN: ['2469-9918', '2469-990X']
DOI: https://doi.org/10.1103/physrevfluids.7.094602