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Infrared Low Temperature Turbine Vane Rough Surface Heat Transfer Measurements

[+] Author Affiliations
R. J. Boyle, C. M. Spuckler, B. L. Lucci, W. P. Camperchioli

NASA Glenn Research Center, Cleveland, OH

Paper No. 2000-GT-0216, pp. V003T01A024; 15 pages
doi:10.1115/2000-GT-0216
From:
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7856-9
  • Copyright © 2000 by ASME

abstract

Turbine vane heat transfer distributions obtained using an infrared camera technique are described. Infrared thermography was used because non-contact surface temperature measurements were desired. Surface temperatures were 80°C or less. Tests were conducted in a three vane linear cascade, with inlet pressures between 0.14 and 1.02atm., and exit Mach numbers of 0.3, 0.7, and 0.9, for turbulence intensities of approximately 1 and 10%. Measurements were taken on the vane suction side, and on the pressure side leading edge region. The designs for both the vane and test facility are discussed. The approach used to account for conduction within the vane is described. Midspan heat transfer distributions are given for the range of test conditions.

Copyright © 2000 by ASME

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