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Measured and Calculated Wall Temperatures on Air-Cooled Turbine Vanes With Boundary Layer Transition PUBLIC ACCESS

[+] Author Affiliations
Curt H. Liebert, Raymond E. Gaugler, Herbert J. Gladden

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Paper No. 83-GT-33, pp. V004T09A003; 8 pages
doi:10.1115/83-GT-33
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 4: Heat Transfer; Electric Power
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7954-2
  • Copyright © 1983 by ASME

abstract

Convection cooled turbine vane metal wall temperatures experimentally obtained in a hot cascade for a given one-vane design were compared with wall temperatures calculated with TACT1 and STAN5 computer codes which incorporated various models for predicting laminar-to-turbulent boundary layer transition. Favorable comparisons on both vane surfaces were obtained at high Reynolds number with only one of these transition models. When other models were used, temperature differences between calculated and experimental data obtained at the high Reynolds number were as much as 14 percent in the separation bubble region of the pressure surface. On the suction surface and at lower Reynolds number, predictions and data unsatisfactorily differed by as much as 22 percent. Temperature differences of this magnitude can represent orders of magnitude error in blade life prediction.

Copyright © 1983 by ASME
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