A meshless method for subsonic stall flutter analysis of turbomachinery 3D blade cascade

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F21%3A00549845" target="_blank" >RIV/61388998:_____/21:00549845 - isvavai.cz</a>

Výsledek na webu

<a href="https://journals.pan.pl/dlibra/publication/139000/edition/120815/content" target="_blank" >https://journals.pan.pl/dlibra/publication/139000/edition/120815/content</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.24425/bpasts.2021.139000" target="_blank" >10.24425/bpasts.2021.139000</a>

Jazyk výsledku

angličtina

Název v původním jazyce

A meshless method for subsonic stall flutter analysis of turbomachinery 3D blade cascade

Popis výsledku v původním jazyce

The analysis of subsonic stall flutter in turbomachinery blade cascade is carried out using a medium-fidelity reduced-order aeroelastic numerical model. The model is a type of field mesh-free approach and based on a hybrid boundary element method. The medium-fidelity flow solver is developed on the principle of viscous-inviscid two-way weak-coupling approach. The hybrid flow solver is employed to model separated flow and stall flutter in the 3D blade cascade at subsonic speed. The aerodynamic damping coefficient w.r.t. inter blade phase angle in traveling-wave mode is estimated along with other parameters. The same stability parameter is used to analyze the cascade flutter resistance regime. The estimated results are validated against experimental measurements as well as Navier-Stokes based high fidelity CFD model. The simulated results show good agreement with experimental data. Furthermore, the hybrid flow solver has managed to bring down the computational cost significantly as compared to mesh-based CFD models. Therefore, all the prime objectives of the research have been successfully achieved.n

Název v anglickém jazyce

A meshless method for subsonic stall flutter analysis of turbomachinery 3D blade cascade

Popis výsledku anglicky

The analysis of subsonic stall flutter in turbomachinery blade cascade is carried out using a medium-fidelity reduced-order aeroelastic numerical model. The model is a type of field mesh-free approach and based on a hybrid boundary element method. The medium-fidelity flow solver is developed on the principle of viscous-inviscid two-way weak-coupling approach. The hybrid flow solver is employed to model separated flow and stall flutter in the 3D blade cascade at subsonic speed. The aerodynamic damping coefficient w.r.t. inter blade phase angle in traveling-wave mode is estimated along with other parameters. The same stability parameter is used to analyze the cascade flutter resistance regime. The estimated results are validated against experimental measurements as well as Navier-Stokes based high fidelity CFD model. The simulated results show good agreement with experimental data. Furthermore, the hybrid flow solver has managed to bring down the computational cost significantly as compared to mesh-based CFD models. Therefore, all the prime objectives of the research have been successfully achieved.n

Druh

J_SC - Článek v periodiku v databázi SCOPUS

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

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 periodika

Polish Academy of Sciences. Bulletin. Technical Sciences

ISSN

0239-7528

e-ISSN

2300-1917

Svazek periodika

69

Číslo periodika v rámci svazku

6

Stát vydavatele periodika

PL - Polská republika

Počet stran výsledku

9

Strana od-do

e139000

Kód UT WoS článku

—

EID výsledku v databázi Scopus

2-s2.0-85122270224