AERODYNAMIC RESEARCH ON THE MCA ? TYPE COMPRESSOR BLADE CASCADE

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

AERODYNAMIC RESEARCH ON THE MCA ? TYPE COMPRESSOR BLADE CASCADE

Popis výsledku v původním jazyce

This paper deals with an analysis of the flow through a high cambered compressor blade cascade. The profiles of the blade cascade have been designed to be of MCA-type. The geometric and aerodynamic parameters of the cascade are presented here. The aerodynamic research was performed in a transonic wind tunnel. Optical methods were applied to obtain information on the flow structures aking place in the interblade channels when operating in a range of subsonic and transonic velocities and at various anglesof incidence. The internal shock waves and the flow separation in the rear part of the cascade channel were bserved and studied. Their influence on the loss coefficient and exit flow angle at subsonic and low transonic region was assessed. The thicknessof the sidewall boundary layer in the interblade channel was measured in order to investigate the development of the axial velocity density ratio (AVDR), which plays an important role in the interpretation of the results.

Název v anglickém jazyce

AERODYNAMIC RESEARCH ON THE MCA ? TYPE COMPRESSOR BLADE CASCADE

Popis výsledku anglicky

This paper deals with an analysis of the flow through a high cambered compressor blade cascade. The profiles of the blade cascade have been designed to be of MCA-type. The geometric and aerodynamic parameters of the cascade are presented here. The aerodynamic research was performed in a transonic wind tunnel. Optical methods were applied to obtain information on the flow structures aking place in the interblade channels when operating in a range of subsonic and transonic velocities and at various anglesof incidence. The internal shock waves and the flow separation in the rear part of the cascade channel were bserved and studied. Their influence on the loss coefficient and exit flow angle at subsonic and low transonic region was assessed. The thicknessof the sidewall boundary layer in the interblade channel was measured in order to investigate the development of the axial velocity density ratio (AVDR), which plays an important role in the interpretation of the results.

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

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)<br>Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2010

Kód důvěrnosti údajů

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

Název statě ve sborníku

Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air GT2010

ISBN

978-0-7918-3872-3

ISSN

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e-ISSN

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Počet stran výsledku

10

Strana od-do

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Název nakladatele

ASME

Místo vydání

Glasgow

Místo konání akce

Glasgow

Datum konání akce

14. 6. 2010

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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