Investigation of Blade Cascade Torsional Flutter Using the Discontinuous Galerkin Approach in Correlation with Experimental Measurements

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F24%3A00598805" target="_blank" >RIV/61388998:_____/24:00598805 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/49777513:23520/24:43973561

Výsledek na webu

<a href="https://www.tandfonline.com/doi/full/10.1080/10618562.2024.2395568" target="_blank" >https://www.tandfonline.com/doi/full/10.1080/10618562.2024.2395568</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1080/10618562.2024.2395568" target="_blank" >10.1080/10618562.2024.2395568</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Investigation of Blade Cascade Torsional Flutter Using the Discontinuous Galerkin Approach in Correlation with Experimental Measurements

Popis výsledku v původním jazyce

In this paper, the conditions under which low subsonic torsional flutter in rotor blades occurs are studied experimentally and numerically using the energy method with the assumption of travelling wave modes. As the test geometry, a blade cascade of five blades is considered. The three middle blades have a rotational degree of freedom, and the two outer blades are stationary. The experiments were performed in a wind tunnel at the Institute of Thermomechanics of the Czech Academy of Sciences. The numerical investigation was carried out using the developed CFD solver based on the discretization of the Favre-averaged Navier-Stokes equations by the discontinuous Galerkin method. A novel mesh-deformation algorithm suitable for fluid flow problems with multiple independently moving bodies is proposed. The CFD solver is benchmarked on test problems of flow around stationary and moving aerofoils. Following the energy method, the middle blades are forced to perform a harmonic pitching motion with various interblade phase angles. The total work per cycle of aerodynamic forces acting on the middle blade is evaluated. This analysis is performed both experimentally and numerically. The experiment measurement and the CFD solver predicted the formation of flutter for the same interblade phase angle. Moreover, qualitative agreement is evident between the experiment and simulation on the evaluated work per cycle for various interblade phase angles.

Název v anglickém jazyce

Investigation of Blade Cascade Torsional Flutter Using the Discontinuous Galerkin Approach in Correlation with Experimental Measurements

Popis výsledku anglicky

In this paper, the conditions under which low subsonic torsional flutter in rotor blades occurs are studied experimentally and numerically using the energy method with the assumption of travelling wave modes. As the test geometry, a blade cascade of five blades is considered. The three middle blades have a rotational degree of freedom, and the two outer blades are stationary. The experiments were performed in a wind tunnel at the Institute of Thermomechanics of the Czech Academy of Sciences. The numerical investigation was carried out using the developed CFD solver based on the discretization of the Favre-averaged Navier-Stokes equations by the discontinuous Galerkin method. A novel mesh-deformation algorithm suitable for fluid flow problems with multiple independently moving bodies is proposed. The CFD solver is benchmarked on test problems of flow around stationary and moving aerofoils. Following the energy method, the middle blades are forced to perform a harmonic pitching motion with various interblade phase angles. The total work per cycle of aerodynamic forces acting on the middle blade is evaluated. This analysis is performed both experimentally and numerically. The experiment measurement and the CFD solver predicted the formation of flutter for the same interblade phase angle. Moreover, qualitative agreement is evident between the experiment and simulation on the evaluated work per cycle for various interblade phase angles.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

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

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2024

Kód důvěrnosti údajů

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

Název periodika

International Journal of Computational Fluid Dynamics

ISSN

1061-8562

e-ISSN

1029-0257

Svazek periodika

38

Číslo periodika v rámci svazku

1

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

15

Strana od-do

45-60

Kód UT WoS článku

001306169400001

EID výsledku v databázi Scopus

2-s2.0-85203242516