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Observations of Wake-Induced Turbulent Spots on an Axial Compressor Blade PUBLIC ACCESS

[+] Author Affiliations
G. J. Walker, W. J. Solomon

University of Tasmania, Hobart, TAS, Australia

J. P. Gostelow

University of Technology, Sydney, Sydney, NSW, Australia

Paper No. 93-GT-378, pp. V03CT17A039; 11 pages
doi:10.1115/93-GT-378
From:
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME

abstract

Measurements of transitional flow in regions of strong adverse pressure gradient on an axial compressor stator are reported. The range of observations covers separating laminar flow at transition onset, and reattachment of intermittently turbulent periodically separated shear layers.

Transition was characterised by the regular appearance of turbulent spots in association with the rotor blade wake disturbances. However, the initial breakdown did not coincide with the wake passage as has usually been observed by other workers. The spots rather evolved from the growth of instability wave packets which lagged the wake passage.

Data presented from the compressor blade measurements include: mean and ensemble-average velocities and associated integral parameters; distributions of total, periodic and random disturbance components; typical individual velocity fluctuation records; contours of ensemble-average random disturbance level; and boundary layer intermittency distributions.

Measurements of turbulent intermittency showed a significant fall in this quantity near the wall in the reattaching flow. This has significant implications for the interpretation of transition data from surface film gage observations.

Copyright © 1993 by ASME
This article is only available in the PDF format.

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