Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Strong Shock-Wave/Boundary Layer Interaction

0495984 - ÚT 2019 RIV CZ eng A - Abstract
Straka, P. - Příhoda, Jaromír - Luxa, Martin
Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Strong Shock-Wave/Boundary Layer Interaction.
Computational Mechanics 2018 - Book of extended abstracts. Plzeň: University of West Bohemia, Plzeň, 2018 - (Adámek, V.; Jonášová, A.). s. 123-124. ISBN 978-80-261-0819-1.
[Conference with international participation Computational Mechanics 2018 /34./. 31.10.2018-02.11.2018, Srní]
R&D Projects: GA TA ČR TH02020057
Institutional support: RVO:61388998
Keywords : turbine cascade * transition model * shock wave-boundary layer interaction
OECD category: Applied mechanics

The contribution deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with the supersonic inlet boundary conditions. The simulation was carried out by the in-house computational programme using the explicit algebraic Reynolds stress model completed by the bypass transition model with the algebraic equation for the intermittency coefficient. Predictions carried out for the nominal conditions were focused on the adequate simulation of the shock-wave/boundary-layer interaction. The outlet boundary condition given the outlet isentropic Mach number was optimised according to angle of the exit shock wave and the blade chord. Numerical results were compared with experimental data.
Permanent Link: http://hdl.handle.net/11104/0289917