Numerical modelling of the experimental based high frequency subsonic stall flutter in linear blade cascade

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F21%3A00549787" target="_blank" >RIV/61388998:_____/21:00549787 - isvavai.cz</a>

Výsledek na webu

<a href="http://repozytorium.p.lodz.pl/handle/11652/4116" target="_blank" >http://repozytorium.p.lodz.pl/handle/11652/4116</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Numerical modelling of the experimental based high frequency subsonic stall flutter in linear blade cascade

Popis výsledku v původním jazyce

Stall flutter in large steam turbine blades is one of the major challenge in the operation safety of turbomachinery. Stall flutter triggers due to complete or partial separation of flow from the blade surfaces when the angles of attack are relatively high, especially in low pressure stages. For the design and development of modern turbomachines prediction of subsonic stall flutter is essential. Numerical simulations are preferred over physical model for stall flutter analysis to save both time and cost. This paper deals with the numerical modelling of the five blade cascade with different flow variables to analyze subsonic stall flutter. Furthermore, in this numerical study various factors dominating the stall flutter phenomenon will be carried out in detail. The numerically estimated stability parameters will be validated against the experimental data obtained from five blade cascade experimental model.nnn

Název v anglickém jazyce

Numerical modelling of the experimental based high frequency subsonic stall flutter in linear blade cascade

Popis výsledku anglicky

Stall flutter in large steam turbine blades is one of the major challenge in the operation safety of turbomachinery. Stall flutter triggers due to complete or partial separation of flow from the blade surfaces when the angles of attack are relatively high, especially in low pressure stages. For the design and development of modern turbomachines prediction of subsonic stall flutter is essential. Numerical simulations are preferred over physical model for stall flutter analysis to save both time and cost. This paper deals with the numerical modelling of the five blade cascade with different flow variables to analyze subsonic stall flutter. Furthermore, in this numerical study various factors dominating the stall flutter phenomenon will be carried out in detail. The numerically estimated stability parameters will be validated against the experimental data obtained from five blade cascade experimental model.nnn

Druh

O - Ostatní výsledky

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