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The Prediction of Surge Margins During Gas Turbine Transients PUBLIC ACCESS

[+] Author Affiliations
N. R. L. Maccallum

University of Glasgow, Glasgow, Scotland

P. Pilidis

Caledonian Airmotive Ltd., Prestwick, Scotland

Paper No. 85-GT-208, pp. V001T03A052; 8 pages
doi:10.1115/85-GT-208
From:
  • ASME 1985 International Gas Turbine Conference and Exhibit
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 18–21, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7938-2
  • Copyright © 1985 by ASME

abstract

This paper describes how allowance for the thermal effects of non-adiabatic flow, altered boundary layer development, changes in tip clearances and changes in seal clearances have been incorporated into a general gas turbine transient program. This program has been applied to a two-spool bypass engine. Revised predictions of surge margins in three common transients have been obtained. When the engine undergoes a “cold” acceleration, the thermal effects on the trajectory and on the surge line give a much increased proportion of unused surge margin in the H.P. Compressor, as compared to adiabatic predictions. In a “hot” acceleration this improvement is considerably reduced.

Copyright © 1985 by ASME
This article is only available in the PDF format.

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