Innovative design of experimental blade cascade model for in-depth analysis of stall flutter

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F24%3A00598764" target="_blank" >RIV/61388998:_____/24:00598764 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/68407700:21220/24:00382385

Výsledek na webu

<a href="https://journals.pan.pl/dlibra/publication/150806/edition/131539/content" target="_blank" >https://journals.pan.pl/dlibra/publication/150806/edition/131539/content</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.24425/bpasts.2024.150806" target="_blank" >10.24425/bpasts.2024.150806</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Innovative design of experimental blade cascade model for in-depth analysis of stall flutter

Popis výsledku v původním jazyce

Stall flutter is a serious threat to the operational integrity in turbomachinery, particularly in the final stage rotors of steam turbines and in compressors. Although computer science has developed rapidly and much of the research can be carried out using numerical tools, thesimulation of some phenomena, such as stall flutter, is still very challenging and needs to be supported by experimental data. This paper presents an innovative experimental linear blade cascade design with five prismatic blades with pitch degrees of freedom, designed to be operated in a low subsonic wind tunnel. The geometry of the blade cascade was chosen on the basis of the experimental and numerical tests to allow stall flutter initiation. New suspension, measurement and electromagnetic excitation systems were developed and experimentally tested to allow accurate measurement of aerodynamic damping during controlled flutter tests. The novelty of the experimental blade cascade is the possibility of single pulse excitation of the blades. The cascade can be brought to the edge of stability by adjusting the angle of attack and flow velocity, and then thenpulse can be used to induce stall flutter. Measurement of both mechanical and flow characteristics, also demonstrated in this paper, will provide data for in-depth analysis of stall flutter initiation and propagation.

Název v anglickém jazyce

Innovative design of experimental blade cascade model for in-depth analysis of stall flutter

Popis výsledku anglicky

Stall flutter is a serious threat to the operational integrity in turbomachinery, particularly in the final stage rotors of steam turbines and in compressors. Although computer science has developed rapidly and much of the research can be carried out using numerical tools, thesimulation of some phenomena, such as stall flutter, is still very challenging and needs to be supported by experimental data. This paper presents an innovative experimental linear blade cascade design with five prismatic blades with pitch degrees of freedom, designed to be operated in a low subsonic wind tunnel. The geometry of the blade cascade was chosen on the basis of the experimental and numerical tests to allow stall flutter initiation. New suspension, measurement and electromagnetic excitation systems were developed and experimentally tested to allow accurate measurement of aerodynamic damping during controlled flutter tests. The novelty of the experimental blade cascade is the possibility of single pulse excitation of the blades. The cascade can be brought to the edge of stability by adjusting the angle of attack and flow velocity, and then thenpulse can be used to induce stall flutter. Measurement of both mechanical and flow characteristics, also demonstrated in this paper, will provide data for in-depth analysis of stall flutter initiation and propagation.

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

Polish Academy of Sciences. Bulletin. Technical Sciences

ISSN

0239-7528

e-ISSN

2300-1917

Svazek periodika

72

Číslo periodika v rámci svazku

5

Stát vydavatele periodika

PL - Polská republika

Počet stran výsledku

11

Strana od-do

e150806

Kód UT WoS článku

001410612000014

EID výsledku v databázi Scopus

2-s2.0-85204785473