Application of boundary element type flow models in turbomachinery stability analysis

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F21%3A00546884" target="_blank" >RIV/61388998:_____/21:00546884 - isvavai.cz</a>

Výsledek na webu

<a href="https://cloudserver048868.home.pl/web/content/archives_icsv_last/2021_icsv27/content/papers/papers/full_paper_178_20210423151446876.pdf" target="_blank" >https://cloudserver048868.home.pl/web/content/archives_icsv_last/2021_icsv27/content/papers/papers/full_paper_178_20210423151446876.pdf</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Application of boundary element type flow models in turbomachinery stability analysis

Popis výsledku v původním jazyce

In this research subsonic flutter in low pressure stage steam turbine blade is studied. A medium fidelity flow solver based on boundary element type method is adopted for numerical flow modeling.nA modified version of 2D surface panel method is used as boundary element method to model the flow field. The subsonic classical flutter and stall flutter in turbomachinery modeled and the aerodynamic damping coefficient w.r.t. inter blade phase angle curve is evaluated for the stability check. The aerodynamic damping coefficient at different inter blade phase angle is estimated using modified panel method flow model for both classical and stall flutter cases. The estimated results is validated against experimental measurements as well Navier-Stokes equation based high fidelity computational fluid dynamics model.n

Název v anglickém jazyce

Application of boundary element type flow models in turbomachinery stability analysis

Popis výsledku anglicky

In this research subsonic flutter in low pressure stage steam turbine blade is studied. A medium fidelity flow solver based on boundary element type method is adopted for numerical flow modeling.nA modified version of 2D surface panel method is used as boundary element method to model the flow field. The subsonic classical flutter and stall flutter in turbomachinery modeled and the aerodynamic damping coefficient w.r.t. inter blade phase angle curve is evaluated for the stability check. The aerodynamic damping coefficient at different inter blade phase angle is estimated using modified panel method flow model for both classical and stall flutter cases. The estimated results is validated against experimental measurements as well Navier-Stokes equation based high fidelity computational fluid dynamics model.n

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20302 - Applied mechanics

Projekt

<a href="/cs/project/GC19-02288J" target="_blank" >GC19-02288J: Robustní metody redukce-řádu modelu pro úlohy interakce poddajných těles s tekutinou</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

8

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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