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Statements

Subject Item
n2:RIV%2F49777513%3A23210%2F10%3A00503637%21RIV11-MSM-23210___
rdf:type
n18:Vysledek skos:Concept
dcterms:description
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 the frequencyof 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 were carried 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 the remaining 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 flow pulsation or 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 the frequencyof 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 were carried 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 the remaining 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 flow pulsation or
dcterms:title
Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel
skos:prefLabel
Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel
skos:notation
RIV/49777513:23210/10:00503637!RIV11-MSM-23210___
n4:aktivita
n13:P
n4:aktivity
P(1M06059)
n4:cisloPeriodika
3
n4:dodaniDat
n8:2011
n4:domaciTvurceVysledku
n16:5496349
n4:druhVysledku
n14:J
n4:duvernostUdaju
n6:S
n4:entitaPredkladatele
n11:predkladatel
n4:idSjednocenehoVysledku
275647
n4:idVysledku
RIV/49777513:23210/10:00503637
n4:jazykVysledku
n15:eng
n4:klicovaSlova
numerical simulation; flow pulsations origin; gas turbine; axial compressor; fatigue failure
n4:klicoveSlovo
n5:axial%20compressor n5:flow%20pulsations%20origin n5:gas%20turbine n5:numerical%20simulation n5:fatigue%20failure
n4:kodStatuVydavatele
US - Spojené státy americké
n4:kontrolniKodProRIV
[E4304177B07C]
n4:nazevZdroje
Journal of Turbomachinery
n4:obor
n7:BK
n4:pocetDomacichTvurcuVysledku
1
n4:pocetTvurcuVysledku
2
n4:projekt
n10:1M06059
n4:rokUplatneniVysledku
n8:2010
n4:svazekPeriodika
132
n4:tvurceVysledku
Polanský, Jiří Cyrus, Václav
s:issn
0889-504X
s:numberOfPages
11
n12:organizacniJednotka
23210