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Unsteady Viscous Flow in a High Speed Core Compressor PUBLIC ACCESS

[+] Author Affiliations
M. A. Cherrett, J. D. Bryce

Royal Aerospace Establishment, Pyestock, Farnborough, Hants, UK

Paper No. 91-GT-091, pp. V001T01A039; 8 pages
doi:10.1115/91-GT-091
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

A probe incorporating a miniature high-frequency response pressure transducer has been traversed behind the first three stages of a high-speed multistage compressor operating at throttle settings corresponding to near choke, peak efficiency and near surge. A novel method of compensating for transducer temperature sensitivity was employed. Consequently, time-averaged pressures derived from the transducer were found to be in good agreement with pneumatic pressure measurements. Analysis of the unsteady pressure measurements revealed both the periodic and random fluctuations in the flowfield. This provided information on rotor-rotor interaction effects and the nature of viscous blade wake and secondary flows in each stage.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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