Analysis for Predicting Adiabatic Wall Temperatures With Single Hole Coolant Injection Into a Low Speed Crossflow FREE

[+] Author Affiliations
C. R. Wang, S. S. Papell, R. W. Graham

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

Paper No. 81-GT-91, pp. V003T09A009; 7 pages
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 3: Heat Transfer; Electric Power
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7963-4
  • Copyright © 1981 by ASME


Assuming the local adiabatic wall temperature equals the local total temperature in a low speed coolant mixing layer, integral conservation equations with and without the boundary layer effects are formulated for the mixing layer downstream of a single coolant injection hole oriented at a 30 degree angle to the crossflow. These equations are solved numerically to determine the center-line local adiabatic wall temperature and the effective coolant coverage area. Comparison of the numerical results with an existing film cooling experiment indicates that the present analysis permits a simplified but reasonably accurate prediction of the centerline effectiveness and coolant coverage area downstream of a single hole crossflow stream wise injection at 30-deg inclination angle.

Copyright © 1981 by ASME
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