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Effects of Surface Roughness on Turbine Vane Heat Transfer

[+] Author Affiliations
R. J. Boyle

NASA Glenn Research Center, Cleveland, OH

R. G. Senyitko

QSS Group, Inc., Cleveland, OH

Paper No. GT2005-69133, pp. 931-942; 12 pages
doi:10.1115/GT2005-69133
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 3: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4726-8 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

Turbine vane surface temperatures were measured in a linear cascade using an infrared non-contact thermal detector. A thermal barrier coating (TBC) was applied to the vane surface to give a rough surface. The temperature drop across the relatively thick TBC was used to determine heat transfer coefficients. Tests were conducted over a range of Reynolds and Mach numbers, resulting in large variations in hydraulic roughness. The measured heat transfer rates were significantly higher than were expected for a smooth vane. The detector was mounted in a probe holder, and traversed in a manner similar to that used for pneumatic or hot wire probes. The results showed that this approach gave useful information, and should be considered when non-contact surface temperatures are desired.

Copyright © 2005 by ASME

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