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Demonstration of Model Based, Off-Line Performance Analysis on a Gas Turbine Air Compressor (GTAC)

[+] Author Affiliations
Ashley P. Wiese, Matthew J. Blom, Michael J. Brear, Chris Manzie

The University of Melbourne, Parkville, VIC, Australia

Anthony Kitchener

SVW Pty Ltd., Spotswood, VIC, Australia

Paper No. GT2012-68825, pp. 185-194; 10 pages
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 3: Cycle Innovations; Education; Electric Power; Fans and Blowers; Industrial and Cogeneration
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4469-4
  • Copyright © 2012 by ASME


This paper presents a model based, off-line method for analysing the performance of individual components in an operating gas turbine. As with other studies, a least squares approach is employed. The component models are physics-based where possible. In its most general form, the method permits simultaneous inference of the combustor efficiency and stagnation pressure loss, the hot-end heat losses and associated heat transfer coefficients, the turbine inlet temperature and the turbine’s isentropic efficiency. As part of this, combustion of unburnt fuel within the turbine is modelled.

The method is demonstrated on a so-called ‘Gas Turbine Air Compressor (GTAC)’ test rig built by the group, a micro-turbine whose compressor supplies air for both the cycle and external applications, but produces no shaft work. The method is also formulated for other gas turbines. The highest order models are tested first, and then the model order is progressively reduced to determine adequate component model complexity. Since the GTAC is a micro-gas turbine, heat losses are found to be significant. It is also shown that care must be taken to distinguish between variations in the performance of different components, since the performance of several components can have similar effects on the complete, operating device.

Copyright © 2012 by ASME



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