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High Resolution Film Cooling Effectiveness Comparison of Axial and Compound Angle Holes on the Suction Side of a Turbine Vane

[+] Author Affiliations
Scot K. Waye, David G. Bogard

University of Texas at Austin, Austin, TX

Paper No. GT2006-90225, pp. 195-203; 9 pages
doi:10.1115/GT2006-90225
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

Film cooling adiabatic effectiveness for axial and compound angle holes on the suction side of a simulated turbine vane was investigated to determine the relative performance of these configurations. The effect of the surface curvature was also evaluated by comparing to previous curvature studies and flat plate film cooling results. Experiments were conducted for varying coolant density ratio, mainstream turbulence levels, and hole spacing. Results from these measurements showed that for mild curvature, 2r/d ≈ 160, flat plate results are sufficient to predict the cooling effectiveness. Furthermore, the compound angle injection improves adiabatic effectiveness for higher blowing ratios, similar to previous studies using flat plate facilities.

Copyright © 2006 by ASME

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