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A Transient Infrared Technique for Measuring Surface and Endwall Heat Transfer in a Transonic Turbine Cascade

[+] Author Affiliations
C. Reagle, A. Newman, S. Xue, W. Ng, S. Ekkad

Virginia Polytechnic Institute and State University, Blacksburg, VA

H. K. Moon, L. Zhang

Solar Turbines Inc., San Diego, CA

Paper No. GT2010-22975, pp. 405-411; 7 pages
doi:10.1115/GT2010-22975
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4399-4 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

This paper describes a method for obtaining surface and endwall heat transfer in an uncooled transonic cascade facility using infrared thermography measurements. Midspan heat transfer coefficient results are first presented for an engine representative first stage nozzle guide vane at exit Mach number of 0.77, Reynolds number of 1.05×106 and freestream turbulence intensity of 16%. The results obtained from infrared thermography are compared with previously published results using thin film gauges in the same facility on the same geometry. There is generally good agreement between the two measurement techniques in both trend and overall level of heat transfer coefficient over the vane surface. Stanton number contours are then presented for a blade endwall at exit Mach number of 0.88, Reynolds number of 1.70×106 and freestream turbulence intensity of 8%. Infrared thermography results are qualitatively compared with results from a published work obtained with liquid crystals at similar flow conditions. Results are qualitatively in agreement.

Copyright © 2010 by ASME

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