Meshfree reduced order model for turbomachinery blade flutter analysis

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F22%3A00556768" target="_blank" >RIV/61388998:_____/22:00556768 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.sciencedirect.com/science/article/pii/S002074032200145X" target="_blank" >https://www.sciencedirect.com/science/article/pii/S002074032200145X</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.ijmecsci.2022.107222" target="_blank" >10.1016/j.ijmecsci.2022.107222</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Meshfree reduced order model for turbomachinery blade flutter analysis

Popis výsledku v původním jazyce

The paper introduces a development and application of boundary element based meshfree reduced order model for subsonic flutter analysis of turbomachinery blade cascade. The prime objective of the present work is to demonstrate the efficient use of meshfree hybrid boundary element method for subsonic flutter analysis of low pressure stage steam turbine blades . The meshfreincompressible fluid solver is developed employing 3D inviscid panel method . To model the flow separation inviscid-PM is hybridized with integral boundary layer approach using inviscid-viscous coupling mechanism along with discrete vortex particle method. A 3D annular test cascade is modeled using proposed meshfree solver for the flutter analysis. The comparison of estimated pressure coefficient and aerodynamic damping highlights a good agreement with experimental data and mesh based CFD-model’s results. Moreover, it have observed that the computational time for flutter analysis using proposed method is significantly lower compared to traditionally used CFD based numerical models for subsonic flutter in 3D blade cascade.

Název v anglickém jazyce

Meshfree reduced order model for turbomachinery blade flutter analysis

Popis výsledku anglicky

The paper introduces a development and application of boundary element based meshfree reduced order model for subsonic flutter analysis of turbomachinery blade cascade. The prime objective of the present work is to demonstrate the efficient use of meshfree hybrid boundary element method for subsonic flutter analysis of low pressure stage steam turbine blades . The meshfreincompressible fluid solver is developed employing 3D inviscid panel method . To model the flow separation inviscid-PM is hybridized with integral boundary layer approach using inviscid-viscous coupling mechanism along with discrete vortex particle method. A 3D annular test cascade is modeled using proposed meshfree solver for the flutter analysis. The comparison of estimated pressure coefficient and aerodynamic damping highlights a good agreement with experimental data and mesh based CFD-model’s results. Moreover, it have observed that the computational time for flutter analysis using proposed method is significantly lower compared to traditionally used CFD based numerical models for subsonic flutter in 3D blade cascade.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20302 - Applied mechanics

Projekt

Výsledek vznikl pri realizaci vícero projektů. Více informací v záložce Projekty.

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2022

Kód důvěrnosti údajů

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

Název periodika

International Journal of Mechanical Sciences

ISSN

0020-7403

e-ISSN

1879-2162

Svazek periodika

222

Číslo periodika v rámci svazku

May

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

18

Strana od-do

107222

Kód UT WoS článku

000798733400002

EID výsledku v databázi Scopus

2-s2.0-85127625644