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Advanced Capabilities for Gas Turbine Engine Performance Simulations

[+] Author Affiliations
A. Alexiou, K. Mathioudakis

National Technical University of Athens, Athens, Greece

E. H. Baalbergen

National Aerospace Laboratory NLR, Amsterdam, The Netherlands

O. Kogenhop, P. Arendsen

National Aerospace Laboratory NLR, Emmeloord, The Netherlands

Paper No. GT2007-27086, pp. 19-28; 10 pages
doi:10.1115/GT2007-27086
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 1: Turbo Expo 2007
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4790-X | eISBN: 0-7918-3796-3
  • Copyright © 2007 by NTUA and NLR

abstract

This paper describes the integration of advanced methods such as component zooming and distributed computing, in an object-oriented simulation environment dedicated to gas turbine engine performance modelling. A 1-D compressor stage stacking method is used to demonstrate three approaches for integrating numerical zooming in an engine model. In the first approach a 1-D compressor model produces a compressor map that is then used in the engine model in place of the default one. In the second approach the results of the 1-D analysis are passed to the 0-D component through appropriate ‘zooming’ scalars. In the final approach the 1-D compressor component directly replaces the 0-D one in the engine model. Distributed computing is realized using Web Services technology. The implementation steps for a distributed scenario are presented. The standalone compressor stage stacking method, in the form of a shared library, is placed in a remote site and can be accessed over the internet through a Web Service Operation (server side). An engine simulation is set up containing a 1-D compressor component which acts as the client for the Web Service operation. Future development of the tool’s advanced capabilities is finally discussed.

Copyright © 2007 by NTUA and NLR

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