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Heat Transfer and Aerodynamics of a High Rim Speed Turbine Nozzle Guide Vane With Profiled End Walls PUBLIC ACCESS

[+] Author Affiliations
K. S. Chana

Defence Research Agency, Farnborough, Hampshire, UK

Paper No. 92-GT-243, pp. V004T09A023; 6 pages
doi:10.1115/92-GT-243
From:
  • ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Cologne, Germany, June 1–4, 1992
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7896-5
  • Copyright © 1992 by ASME

abstract

It has been shown that the secondary flows present within turbine nozzle guide vanes have a marked effect on heat transfer. The horse-shoe and passage vortices, for example, have a major impact on platform and vane suction surface heat transfer. To investigate these effects further, heat transfer and aerodynamic measurements have been made on an annular transonic turbine nozzle guide vane ring, with three different platform geometries. The measurements were taken in the Isentropic Light Piston test facility at RAE Pyestock at representative values of engine Reynolds number, Mach number and freestream gas-to-wall temperature ratio.

This paper compares and discusses the measured platform and vane suction surface Nusselt and Mach number distributions for the three different endwall profiles. Comparisons with theoretical flow and heat transfer predictions are presented.

Copyright © 1992 by ASME
This article is only available in the PDF format.

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