Subsonic Stall Flutter of a Linear Turbine Blade Cascade Using Experimental and CFD Analysis

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F49193864%3A_____%2F20%3AN0000002" target="_blank" >RIV/49193864:_____/20:N0000002 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/49777513:23210/20:43972854

Výsledek na webu

<a href="https://asmedigitalcollection.asme.org/IMECE/proceedings-abstract/IMECE2020/84546/V07AT07A026/1099223" target="_blank" >https://asmedigitalcollection.asme.org/IMECE/proceedings-abstract/IMECE2020/84546/V07AT07A026/1099223</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1115/IMECE2020-23356" target="_blank" >10.1115/IMECE2020-23356</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Subsonic Stall Flutter of a Linear Turbine Blade Cascade Using Experimental and CFD Analysis

Popis výsledku v původním jazyce

Stall flutter of long blades influences the operation safety of the large steam turbines in off-design conditions. As angles of attack are typically high, a partial or complete separation of the flow from the blade surface occurs. The prediction of stall flutter of turbine blades is a crucial task in the design and development of modern turbomachinery units and reliable design tools are necessary. In this work, aerodynamic stability of a linear turbine blade cascade is tested experimentally at high angle of attack +15°, Ma = 0.2 and the reduced frequency of 0.38. Controlled flutter testing has been performed in a travelling wave mode approach for the torsion with the motion amplitude of 0.5°. In addition, ANSYS CFX with SST k-ω turbulent model is used for URANS simulations of a full-scale computational domain. A separation bubble formed on suction surface near the leading edge has been found in CFD results for each blade. Excellent agreement between the experimental and numerical results in stability maps has been achieved for this case under investigation. This is encouraging and both experimental and numerical techniques will be tested further.

Název v anglickém jazyce

Subsonic Stall Flutter of a Linear Turbine Blade Cascade Using Experimental and CFD Analysis

Popis výsledku anglicky

Stall flutter of long blades influences the operation safety of the large steam turbines in off-design conditions. As angles of attack are typically high, a partial or complete separation of the flow from the blade surface occurs. The prediction of stall flutter of turbine blades is a crucial task in the design and development of modern turbomachinery units and reliable design tools are necessary. In this work, aerodynamic stability of a linear turbine blade cascade is tested experimentally at high angle of attack +15°, Ma = 0.2 and the reduced frequency of 0.38. Controlled flutter testing has been performed in a travelling wave mode approach for the torsion with the motion amplitude of 0.5°. In addition, ANSYS CFX with SST k-ω turbulent model is used for URANS simulations of a full-scale computational domain. A separation bubble formed on suction surface near the leading edge has been found in CFD results for each blade. Excellent agreement between the experimental and numerical results in stability maps has been achieved for this case under investigation. This is encouraging and both experimental and numerical techniques will be tested further.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20303 - Thermodynamics

Projekt

<a href="/cs/project/TN01000007" target="_blank" >TN01000007: Národní centrum pro energetiku</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2020

Kód důvěrnosti údajů

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

Název statě ve sborníku

ASME 2020: International Mechanical Engineering Congress and Exposition

ISBN

978-0-7918-8454-6

ISSN

—

e-ISSN

—

Počet stran výsledku

6

Strana od-do

—

Název nakladatele

ASME

Místo vydání

USA

Místo konání akce

Virtual, Online

Datum konání akce

16. 11. 2020

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

—