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Redesign of an 11-Stage Axial Compressor for Industrial Gas Turbine

[+] Author Affiliations
Koji Terauchi, Daisuke Kariya, Seiichirou Maeda, Kenichirou Yoshiura

Kawasaki Heavy Industries, Ltd., Akashi, Hyogo, Japan

Paper No. GT2005-68689, pp. 261-267; 7 pages
doi:10.1115/GT2005-68689
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

Outlined in this paper are the details of redesign of an 11-stage axial compressor for 18MW class industrial gas turbine. Although the design value of adiabatic efficiency is 85%, the efficiency achieved in the prototype engine test was 1 point short of the target. According to the test results and CFD analyses, it was estimated that the stage mismatching due to an excessive work of intermediate stages was a major cause of the losses. To improve the matching, redesign of airfoils were carried out to some blades and vanes. The results of Multistage CFD showed that the matching was improved and the efficiency was increased, which was also confirmed by the engine test.

Copyright © 2005 by ASME

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