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Design and Development of a 12:1 Pressure Ratio Compressor for the Ruston 6-MW Gas Turbine PUBLIC ACCESS

[+] Author Affiliations
F. Carchedi, G. R. Wood

Ruston Gas Turbines Ltd, Lincoln, England

Paper No. 82-GT-20, pp. V001T01A012; 12 pages
doi:10.1115/82-GT-20
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

This paper describes the design and development of a 15-stage axial flow compressor for a −6MW industrial gas turbine. Detailed aspects of the aerodynamic design are presented together with rig test data for the complete characteristic including stage data. Predictions of spanwise flow distributions are compared with measured values for the front stages of the compressor. Variable stagger stator blading is used to control the position of the low speed surge line and the effects of the stagger changes are discussed.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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