Shock wave boundary layer interaction in profile cascades representing rotor bladings of the last stage of large output steam turbines

Kód výsledku v IS VaVaI

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Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Shock wave boundary layer interaction in profile cascades representing rotor bladings of the last stage of large output steam turbines

Popis výsledku v původním jazyce

This paper is mainly focused on selected interaction phenomena occurring in the root, middle and tip section of the last stage rotor blading consisting of titanium blades Doosan Skoda 1375mm (54") and steel blades Doosan Skoda 1220mm (48"). Measurements and CFD simulations of the flow in selected sections along the blading radius show different types of interaction. Typically for the parts of the blade closer to the hub, only interaction of internal branch of exit shock wave with the suction side boundary layer takes place. At the blade tip where the flow is supersonic at both inlet and outlet, interaction of internal branch of inlet shock wave with the pressure side boundary layer occurs. The "reflected", additional shock wave arising from this interaction affect the flow field close to the suction side of the adjacent profile. The structure of interaction often depends on the flow conditions (nominal conditions and off-design conditions of flow, incl. different inlet flow angles).

Název v anglickém jazyce

Shock wave boundary layer interaction in profile cascades representing rotor bladings of the last stage of large output steam turbines

Popis výsledku anglicky

This paper is mainly focused on selected interaction phenomena occurring in the root, middle and tip section of the last stage rotor blading consisting of titanium blades Doosan Skoda 1375mm (54") and steel blades Doosan Skoda 1220mm (48"). Measurements and CFD simulations of the flow in selected sections along the blading radius show different types of interaction. Typically for the parts of the blade closer to the hub, only interaction of internal branch of exit shock wave with the suction side boundary layer takes place. At the blade tip where the flow is supersonic at both inlet and outlet, interaction of internal branch of inlet shock wave with the pressure side boundary layer occurs. The "reflected", additional shock wave arising from this interaction affect the flow field close to the suction side of the adjacent profile. The structure of interaction often depends on the flow conditions (nominal conditions and off-design conditions of flow, incl. different inlet flow angles).

Druh

D - Stať ve sborníku

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 statě ve sborníku

ECCOMAS Congress 2016 - Proceedings of the 7th European Congress on Computational Methods in Applied Sciences and Engineering

ISBN

978-618828440-1

ISSN

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e-ISSN

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Počet stran výsledku

10

Strana od-do

1464-1473

Název nakladatele

National Technical University of Athens

Místo vydání

Athény

Místo konání akce

Crete

Datum konání akce

5. 6. 2016

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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