Numerical simulations of the 2D supersonic flow through the tip-section turbine blade cascade with a flat profile

Authors

  • Josef Musil Faculty of Mech. Eng., CTU in Prague Institute of Thermomechanics, Academy of Sciences of the Czech Republic
  • Jaromír Příhoda Institute of Thermomechanics, Academy of Sciences of the Czech Republic
  • Jiří Fürst Faculty of Mech. Eng., CTU in Prague

DOI:

https://doi.org/10.24132/acm.2021.621

Keywords:

supersonic tip-section blade cascade, CFD, transition modelling

Abstract

Numerical simulations of 2D compressible flow through the tip-section turbine blade cascade with a flat profile and the supersonic inlet were carried out by the OpenFOAM code using the Favre-averaged Navier-Stokes equations completed by the γ-Re_θt bypass transition model with the SST turbulence model. Predictions completed for nominal regimes were concentrated particularly on the effect of the shock-wave/boundary layer interaction on the transition to turbulence. Further, the link between the inlet Mach number and the inlet flow angle i.e. the so called unique incidence rule was studied. Obtained numerical results were compared with experimental data covering optical and pressure measurements.

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Published

31-Dec-2021

Issue

Vol. 15 No. 2 (2021)

Section

Articles

License

Copyright (c) 2021 Applied and Computational Mechanics

Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

How to Cite

“Numerical simulations of the 2D supersonic flow through the tip-section turbine blade cascade with a flat profile” (2021) Applied and Computational Mechanics, 15(2). doi:10.24132/acm.2021.621.