Heat Transfer Measurements on a Turbine Airfoil at Various Reynolds Numbers and Turbulence Intensities Including Effects of Surface Roughness PUBLIC ACCESS

[+] Author Affiliations
A. Hoffs, U. Drost, A. Bölcs

Swiss Federal Institute of Technology, Lausanne, Switzerland

Paper No. 96-GT-169, pp. V004T09A007; 8 pages
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7875-0
  • Copyright © 1996 by ASME


This paper presents heat transfer measurements on a turbine airfoil in a linear cascade at various exit Reynolds and Mach numbers ranging from 3.2e5 to 1.6e6 and 0.2 to 0.8, respectively, which have been conducted with the transient liquid crystal technique. Two series were performed at turbulence intensities of 5.5% and 10%, the latter being created by a squared-bar mesh placed 10 meshsizes upstream of the turbine airfoils. While normally polished liquid crystals were used additional experiments were done at the high turbulence intensity with naturally rough liquid crystals.

All measurements indicate a gradual increase in heat transfer and an upstream shift of the laminar-to-turbulent transition with increasing Reynolds number and turbulence intensity. The leading edge heat transfer agrees well with correlations if the turbulence length scale is taken into account. The measurements conducted with rough liquid crystals show an earlier transition on the suction side. Calculations with a two-dimensional boundary layer code agree well with the measurements.

Copyright © 1996 by ASME
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