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Detailed Boundary Layer Measurements on a Transonic Turbine Cascade FREE

[+] Author Affiliations
D. J. Mee, M. L. G. Oldfield

University of Oxford, UK

N. C. Baines

Imperial College, UK

Paper No. 90-GT-263, pp. V001T01A092; 11 pages
doi:10.1115/90-GT-263
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME

abstract

The boundary layers of a transonic turbine blade have been measured in detail. The full velocity profiles have been measured at a number of stations on both the suction and pressure surfaces, at conditions representative of engine operation, using a pitot traverse technique and a large scale (300 mm chord) linear cascade. This information has made it possible to follow the development of the boundary layers, initially laminar, through a region of natural transition to a fully developed turbulent layer. Comparisons with other, less detailed, measurements on the same profile using pitot traverse and surface mounted thin films confirm the essential features of the boundary layers.

Copyright © 1990 by ASME
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