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Effect of Stagnation Regions on Film Cooling Effectiveness

[+] Author Affiliations
S. Rodríguez, S. Kersten, H. A. Zuniga, J. C. Ling, J. S. Kapat

University of Central Florida, Orlando, FL

Paper No. GT2007-28001, pp. 781-788; 8 pages
doi:10.1115/GT2007-28001
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME

abstract

Over the last decades, researchers have investigated many aspects of film cooling. The present study investigates the impact of stagnation region created by a downstream airfoil on endwall film cooling effectiveness. Experimental measurements are presented for a single row of cylindrical holes inclined at 35° with hole length to diameter ratio, L/D = 7.5, pitch to diameter ratio, PI/D = 3 with a constant density ratio of 1.26 and with nitrogen as the coolant. Five different configurations were studied. Configuration 0 is the baseline, this configuration consist of a single row of cylindrical holes. Configuration I-III consisted of an airfoil positioned downstream of the injection point at x/D = 6.4, 12.7 and 25.4. The presence of wake is also investigated on configuration IV. This configuration in addition to the airfoil, also has a wake plate at x/D = −12.7, upstream of the injection location. The experimental data shows that slightly higher averaged effectiveness values are observed for configuration I for low blowing ratios. Configuration III average effectiveness is higher for mid and high blowing ratios. For all configurations, the average effectiveness increase with increasing blowing ratio at a x/D further downstream of the injection point where the jet has reattached. Higher blowing ratio increase lateral spreading of the jet promoting jet to jet interaction and mainstream interaction enhancing mixing.

Copyright © 2007 by ASME
Topics: Cooling

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