Experimental setup and measurement for evaluation of blade cascade stall flutter instability

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F21%3A00546845" target="_blank" >RIV/61388998:_____/21:00546845 - isvavai.cz</a>

Výsledek na webu

<a href="https://cloudserver048868.home.pl/web/content/archives_icsv_last/2021_icsv27/content/papers/papers/full_paper_221_20210413121637805.pdf" target="_blank" >https://cloudserver048868.home.pl/web/content/archives_icsv_last/2021_icsv27/content/papers/papers/full_paper_221_20210413121637805.pdf</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Experimental setup and measurement for evaluation of blade cascade stall flutter instability

Popis výsledku v původním jazyce

This paper describes the design of 2D blade cascade for torsional flutter experiment in turbomachinery. The goal of this experimental set-up is to extend our previous research where we used five blade cascade of same dimensions with only translational motion of the blades. The newly built cascade is designed so that the flow incident angle and stagger angle of the cascade can be changed easily to measure different configurations. It is equipped with five symmetrical NACA 0010 airfoil blades which can be changed to different profiles. The cascade is designed to ensure the zero tip clearance effect on the blade tip. Thus, the flow field in the middle of the channel can be considered twodimensional and the measured data will serve us for tuning of reduced order methods developed for flutter calculations. Experimental set-up and first measurement results for one blade are shown in this paper.

Název v anglickém jazyce

Experimental setup and measurement for evaluation of blade cascade stall flutter instability

Popis výsledku anglicky

This paper describes the design of 2D blade cascade for torsional flutter experiment in turbomachinery. The goal of this experimental set-up is to extend our previous research where we used five blade cascade of same dimensions with only translational motion of the blades. The newly built cascade is designed so that the flow incident angle and stagger angle of the cascade can be changed easily to measure different configurations. It is equipped with five symmetrical NACA 0010 airfoil blades which can be changed to different profiles. The cascade is designed to ensure the zero tip clearance effect on the blade tip. Thus, the flow field in the middle of the channel can be considered twodimensional and the measured data will serve us for tuning of reduced order methods developed for flutter calculations. Experimental set-up and first measurement results for one blade are shown in this paper.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20302 - Applied mechanics

Projekt

<a href="/cs/project/GA20-26779S" target="_blank" >GA20-26779S: Výzkum nestabilit dynamického stall flutteru a jejich následků na aplikace turbostrojů pomocí matematických, numerických a experimentálních metod</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2021

Kód důvěrnosti údajů

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

Název statě ve sborníku

27th International Congress on Sound and Vibration: ICSV27

ISBN

978-83-7880-799-5

ISSN

2329-3675

e-ISSN

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Počet stran výsledku

5

Strana od-do

172047

Název nakladatele

Silesian University Press

Místo vydání

Gliwice, Poland

Místo konání akce

Virtual, Online

Datum konání akce

11. 7. 2021

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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