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Compressor Rubbing Risk Analyses for Combustion Turbine Using Thermomechanical and Dynamical FE Modeling

[+] Author Affiliations
Franck T. Meissonnier, Carlo M. Stoisser

Electricité de France, Clamart Cedex, France

Paper No. GT2006-90835, pp. 691-700; 10 pages
doi:10.1115/GT2006-90835
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 5: Marine; Microturbines and Small Turbomachinery; Oil and Gas Applications; Structures and Dynamics, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4240-1 | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

Combustion Turbines operators have recently experienced compressor rubbing related problems during Hot Restart transients. Based on maintenance feedback from in-service combustion turbine, some turbo machinery designers have imposed Hot Restart Restriction and have considered prudent to increase the rotor-to-stator clearances. Combustion Turbines operators have recently experienced compressor rubbing related problems during Hot Restart transients. Based on maintenance feedback from in-service combustion turbine, some turbo machinery designers have imposed Hot Restart Restriction and have considered prudent to increase the rotor-to-stator clearances. Hot Restart has a significant impact on compressor clearances since temperature distribution hasn’t reach its steady-state condition due to heat conduction. When Hot-Restart occurs, thermal distortions of the casing and the bladed rotor are indeed continually evolving. The resulting rotor-to-stator clearances may become extremely low while the rotor expands rapidly due to inertial body forces generated by rotor speed up and vibrates due to mass-unbalance. As a consequence, clearances may dramatically decrease until rubbing occurs. A Finite Element-based analysis has been developed for simulating the time-transient thermo mechanical and the vibratory motion responses of a F-Class combustion turbine. The thermo mechanical responses enable to calculate thermal distortions of the casing and the bladed rotor as well as the rotor expansion due to the inertial body forces generated by rotor speed up. The dynamical responses enable to calculate the amplitude of the shaft line vibration due to mass-unbalance. The approach developed by EDF R&D relies on a 3D thermo mechanical modeling of the compressor rotor/casing and a 1D beam-type modeling of the whole combustion turbine shaft line using Finite Element Code Code_Aster® and Rotor Dynamics Code CADYAC, respectively, developed by EDF R&D. The FE-Models have been validated by comparing compressor tip clearance measurements published by a F-Class manufacturer and FE calculations during a typical start-stop cycle. The FE-predictions obtained with such models are in acceptable agreement with measurements data. The FE models are then used to predict the evolution of the rotor-to-stator clearances and to evaluate the compressor rubbing risk during Hot Restart. The results are then compared with Hot Restart time-restriction imposed by the turbo machinery designer.

Copyright © 2006 by ASME

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