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Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine PUBLIC ACCESS

[+] Author Affiliations
R. C. Kingcombe, S. P. Harasgama, N. P. Leversuch, E. T. Wedlake

Royal Aerospace Establishment, Pyestock, Farnborough, Hampshire, UK

Paper No. 89-GT-228, pp. V001T01A091; 7 pages
doi:10.1115/89-GT-228
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

A high rim speed turbine, incorporating some 3-D features has been designed and tested at RAE Pyestock. There has been cold flow turbine testing, with overall performance measurements, rotor exit traversing as well as surface static pressure measurements on the vane and rotor. The vane has also been tested in annular cascade on the Isentropic Light Piston Cascade giving surface heat transfer measurements on the vanes and endwalls as well as aerodynamic information.

The data have been used to compare with design predictions and the reasons for the differences observed, particularly on the rotor blade, are explored.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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