Effect of Various Boundary Conditions on the Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Flat Profile

0511865 - ÚT 2020 RIV CZ eng C - Conference Paper (international conference)
Musil, Josef - Příhoda, Jaromír - Fürst, J.
Effect of Various Boundary Conditions on the Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Flat Profile.
Proceedings of Computational mechanics 2019. Plzeň: University of West Bohemia, 2019 - (Adámek, V.; Jonášová, A.; Plánička, S.; Zajíček, M.), s. 133-134. ISBN 978-80-261-0889-4.
[Conference with international participation Computational mechanics 2019. Srní (CZ), 04.11.2019-06.11.2019]
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 paper deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with a flat profile. The OpenFOAM code was used for simulations based on the Favre-averaged Navier-Stokes equations completed by the two-equation SST turbulence model and the gama-Re_th transition model proposed by Langtry and Menter (2009). Calculations were carried out for two nominal regimes with the inlet Mach number M1 = 1.2 and isentropic outlet Mach numbers M2is = 1.7 and 1.9. Simulations of compressible flow with the supersonic inlet were focused on the relation between of the inlet Mach number and the inlet angle given by the unique incidence rule. Further, the effect of the inlet free-stream turbulence and of the outlet isentropic Mach number on the flow filed in the blade cascade was investigated. Numerical results were compared with results of optical and pressure measurements.
Permanent Link: http://hdl.handle.net/11104/0304531