Investigation of the Compressible Flow through the Tip-Section Turbine Blade Cascade with Supersonic Inlet

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F16%3AN0000094" target="_blank" >RIV/00010669:_____/16:N0000094 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/61388998:_____/16:00458760

Výsledek na webu

<a href="http://link.springer.com/article/10.1007%2Fs11630-016-0844-0" target="_blank" >http://link.springer.com/article/10.1007%2Fs11630-016-0844-0</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1007/s11630-016-0844-0" target="_blank" >10.1007/s11630-016-0844-0</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Investigation of the Compressible Flow through the Tip-Section Turbine Blade Cascade with Supersonic Inlet

Popis výsledku v původním jazyce

The contribution deals with the experimental and numerical investigation of compressible flow through the tip-section turbine blade cascade with the blade 54″ long. Experimental investigations by means of optical (interferometry and schlieren method) and pneumatic measurements provide more information about the behaviour and nature of basic phenomena occurring in the profile cascade flow field. The numerical simulation was carried out by means of the EARSM turbulence model according to Hellsten (2004) completed by the bypass transition model with the algebraic equation for the intermittency coefficient proposed by Straka and Příhoda [6] and implemented into the in-house numerical code. The investigation was focused particularly on the effect of shock waves on the shear layer development including the laminar/turbulent transition. Interactions of shock waves with shear layers on both sides of the blade result usually in the transition in attached and/ or separated flow and so to the considerable impact to the flow structure and energy losses in the blade cascade.

Název v anglickém jazyce

Investigation of the Compressible Flow through the Tip-Section Turbine Blade Cascade with Supersonic Inlet

Popis výsledku anglicky

The contribution deals with the experimental and numerical investigation of compressible flow through the tip-section turbine blade cascade with the blade 54″ long. Experimental investigations by means of optical (interferometry and schlieren method) and pneumatic measurements provide more information about the behaviour and nature of basic phenomena occurring in the profile cascade flow field. The numerical simulation was carried out by means of the EARSM turbulence model according to Hellsten (2004) completed by the bypass transition model with the algebraic equation for the intermittency coefficient proposed by Straka and Příhoda [6] and implemented into the in-house numerical code. The investigation was focused particularly on the effect of shock waves on the shear layer development including the laminar/turbulent transition. Interactions of shock waves with shear layers on both sides of the blade result usually in the transition in attached and/ or separated flow and so to the considerable impact to the flow structure and energy losses in the blade cascade.

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

BK - Mechanika tekutin

OECD FORD obor

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Projekt

Výsledek vznikl pri realizaci vícero projektů. Více informací v záložce Projekty.

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2016

Kód důvěrnosti údajů

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

Název periodika

Journal of Thermal Science

ISSN

1003-2169

e-ISSN

—

Svazek periodika

25

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

CN - Čínská lidová republika

Počet stran výsledku

7

Strana od-do

138-144

Kód UT WoS článku

000372382600005

EID výsledku v databázi Scopus

2-s2.0-84977143038