Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F49777513%3A23210%2F10%3A00503637" target="_blank" >RIV/49777513:23210/10:00503637 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel

Popis výsledku v původním jazyce

Fatigue failure of the last three stator rows vanes (S17,EGV1, and EGV2) in the 17 stage gas turbine axial compressor occurred in the power plant whwre low calorific fuel syngas, was used.Causes of this dangerous phenomenon were flow pulsations with thefrequencyof 380 - 400 Hz that were found by the experimental investigation of the duty gas turbine. Mechanism of the flow unsteadiness origin was studied with the help of flow simulations in the 2D stator cascade system. Three numerical experiments werecarried out. The first experiment investigated the flow simulation in the stator cascade system with a steady undisturbed inlet flow with increased turbulence intensity. Obtained data did not meet the standards of the actual compressor operations. In theremaining two numerical experiments, a purposely designed rotor cascade was located in front of the stator cascades. Shedding of vortex structures from the cascades profile surfaces at positive incidence angles is responsible for the flo

Název v anglickém jazyce

Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel

Popis výsledku anglicky

Fatigue failure of the last three stator rows vanes (S17,EGV1, and EGV2) in the 17 stage gas turbine axial compressor occurred in the power plant whwre low calorific fuel syngas, was used.Causes of this dangerous phenomenon were flow pulsations with thefrequencyof 380 - 400 Hz that were found by the experimental investigation of the duty gas turbine. Mechanism of the flow unsteadiness origin was studied with the help of flow simulations in the 2D stator cascade system. Three numerical experiments werecarried out. The first experiment investigated the flow simulation in the stator cascade system with a steady undisturbed inlet flow with increased turbulence intensity. Obtained data did not meet the standards of the actual compressor operations. In theremaining two numerical experiments, a purposely designed rotor cascade was located in front of the stator cascades. Shedding of vortex structures from the cascades profile surfaces at positive incidence angles is responsible for the flo

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

BK - Mechanika tekutin

OECD FORD obor

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Projekt

<a href="/cs/project/1M06059" target="_blank" >1M06059: Progresivní technologie a systémy pro energetiku</a><br>

Návaznosti

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

Rok uplatnění

2010

Kód důvěrnosti údajů

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

Název periodika

Journal of Turbomachinery

ISSN

0889-504X

e-ISSN

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Svazek periodika

132

Číslo periodika v rámci svazku

3

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

11

Strana od-do

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Kód UT WoS článku

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EID výsledku v databázi Scopus

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