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The Design and Test of a Two Stage Transonic Axial Flow Compressor PUBLIC ACCESS

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

Ruston Gas Turbines Ltd, Lincoln, England

Paper No. 89-GT-164, pp. V001T01A069; 8 pages
doi:10.1115/89-GT-164
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

The design of the transonic stages, which form the front two stages of a multi stage compressor, is described. The first stage tip Mach No. is 1.1.

The test programme to evaluate the performance of the two stages is outlined and detailed results of the overall and stage performance are presented. Details of the flow field from traverse measurements and the over tip shock structure obtained from high response pressure transducers are compared with predictions.

Strain Gauge results taken from the rotating blades are also presented.

Copyright © 1989 by ASME
Topics: Design , Axial flow
This article is only available in the PDF format.

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