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

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F18%3A00495984" target="_blank" >RIV/61388998:_____/18:00495984 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

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

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

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

Popis výsledku anglicky

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.

Druh

O - Ostatní výsledky

CEP obor

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OECD FORD obor

20302 - Applied mechanics

Projekt

<a href="/cs/project/TH02020057" target="_blank" >TH02020057: Profilové turbínové mříže pro supersonická proudová pole</a><br>

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2018

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů