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

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F21%3A00549456" target="_blank" >RIV/61388998:_____/21:00549456 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/68407700:21220/21:00355868

Výsledek na webu

<a href="https://www.kme.zcu.cz/acm/acm/article/view/621/568" target="_blank" >https://www.kme.zcu.cz/acm/acm/article/view/621/568</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.24132/acm.2021.621" target="_blank" >10.24132/acm.2021.621</a>

Jazyk výsledku

angličtina

Název v původním jazyce

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

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

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

Popis výsledku anglicky

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.

Druh

J_SC - Článek v periodiku v databázi SCOPUS

CEP obor

—

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

2021

Kód důvěrnosti údajů

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

Název periodika

Applied and Computational Mechanics

ISSN

1802-680X

e-ISSN

—

Svazek periodika

15

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

10

Strana od-do

175-184

Kód UT WoS článku

—

EID výsledku v databázi Scopus

2-s2.0-85124559833