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Improved Compressor Exit Diffuser for an Industrial Gas Turbine

[+] Author Affiliations
U. Orth, H. Ebbing

MAN Turbomaschinen AG GHH BORSIG, Oberhausen, Germany

H. Krain, A. Weber, B. Hoffmann

German Aerospace Center (DLR), Cologne, Germany

Paper No. 2001-GT-0323, pp. V001T03A025; 10 pages
doi:10.1115/2001-GT-0323
From:
  • ASME Turbo Expo 2001: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • New Orleans, Louisiana, USA, June 4–7, 2001
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7850-7
  • Copyright © 2001 by ASME

abstract

Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multi stage compressor, composed of a 10 stage axial and a single stage centrifugal compressor, would improve by 0.8% if the efficiency of the back stage centrifugal unit could be raised by 4%. It was expected that this would result in a noticeable improvement of the thermal gas turbine efficiency.

The paper describes the aerodynamical design process used for the stage optimization applying today’s advanced design tools for blade generation and three dimensional aerodynamic calculation methods. Additionally it describes the manufacturing procedure for the resulting three-dimensional blades and the experimental verification of the design approach.

Copyright © 2001 by ASME

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