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 where low calorific fuel syngas, was used. Causes of this dangerous phenomenon were flow pulsations with the frequency of 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 cascade profile surfaces at positive incidence angles is responsible for the flow pulsation origin. The interaction of rotor wakes/stator S17 cascade plays an important role in the investigated phenomenon, as follows from CFD data. Aerodynamic loading of both cascades is equal in the second group of numerical experiments. Computed results were in good qualitative agreement with the experimental ones. As the flow in rotor cascade was not separated, owing to the different aerodynamic loading of rotor and stator S17 cascades, the vortices shedding in stator cascade S17 had a significantly higher frequency of than in other investigated cases.
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July 2010
Research Papers
Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel
Vaclav Cyrus,
e-mail: cyrus.aht@iol.cz
Vaclav Cyrus
AHT Energetics Ltd.
, Podnikatelska 550, Prague-Bechovice, Prague 19011, Czech Republic
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Jiri Polansky
Jiri Polansky
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Vaclav Cyrus
AHT Energetics Ltd.
, Podnikatelska 550, Prague-Bechovice, Prague 19011, Czech Republice-mail: cyrus.aht@iol.cz
Jiri Polansky
J. Turbomach. Jul 2010, 132(3): 031012 (11 pages)
Published Online: March 25, 2010
Article history
Received:
March 10, 2009
Revised:
April 17, 2009
Online:
March 25, 2010
Published:
March 25, 2010
Citation
Cyrus, V., and Polansky, J. (March 25, 2010). "Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel." ASME. J. Turbomach. July 2010; 132(3): 031012. https://doi.org/10.1115/1.3153306
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