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Performance Enhancements to the Industrial Avon Gas Turbine

[+] Author Affiliations
Jerry Blackburn, Gary Frendt, Martine Gagné, Jean-Daniel Genest, Brian Nolan

Rolls-Royce, Montreal, QC, Canada

Toby Kohler

Rolls-Royce, Bristol, UK

Paper No. GT2007-28315, pp. 1521-1530; 10 pages
doi:10.1115/GT2007-28315
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME

abstract

This paper summarises the design, development and validation work of a package of modifications made to the well-established Avon aero derivative gas turbine. Modern turbine aerofoil design technologies were applied to the Avon hot end section, resulting in significant performance enhancements of the engine in terms of heat rate and power. A summary of the key design changes is made and the experimental validation data is reviewed. The implications of the design changes to the engine operational characteristics and component lifing implications where applicable are also reviewed. Key performance data is also presented in the paper.

Copyright © 2007 by ASME
Topics: Gas turbines

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