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A Study of the Prediction of Tip and Seal Clearances and Their Effects in Gas Turbine Transients PUBLIC ACCESS

[+] Author Affiliations
P. Pilidis

Caledonian Airmotive Ltd., Prestwick, Scotland

N. R. L. Maccallum

University of Glasgow, Glasgow, Scotland

Paper No. 84-GT-245, pp. V001T01A074; 9 pages
doi:10.1115/84-GT-245
From:
  • ASME 1984 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 4–7, 1984
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7946-7
  • Copyright © 1984 by ASME

abstract

Clearances of compressor and turbine blade tips and seals alter during and following speed transients. These changes affect the performance of the components and hence of the engine.

This paper describes models for the prediction of blade tip clearance changes and seal clearance changes. These models have been applied to the H.P. Compressor and H.P. Turbine and to two seals controlling air flows in a Two-spool Bypass Engine. The predicted acceleration rates appear to be more influenced by the changes in the seal clearances than by the tip clearance changes.

The increases in computing time in the engine transient program which result from inclusion of the model are acceptable.

Copyright © 1984 by ASME
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