Comparison of Predicted and Experimental External Heat Transfer Around a Film Cooled Cylinder in Crossflow PUBLIC ACCESS

[+] Author Affiliations
Francis S. Stepka, Raymond E. Gaugler

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

Paper No. 83-GT-47, pp. V004T09A004; 11 pages
  • 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


Calculations were made of the film cooling provided by rows of holes around the circumference of a cylinder in crossflow and the results were compared to experimental data obtained from a NASA grant to Purdue University. The calculations and experimental data were for conditions that simulate most of those that are typical of air cooled turbine vane leading edges. Injection was from single and multiple rows of holes located at different angular locations from the stagnation line. The holes in the rows were angled normal to the flow direction and at a 25 degree angle to the cylinder wall. The calculations and experimental data were for several constant values of blowing ratios for all rows and for different blowing ratios for each row, representing a simulation of a common coolant plenum supply to multiple rows of holes. The calculations were made using a finite difference boundary layer code, STAN5, developed under NASA contract with Stanford University and modified at the NASA Lewis Research Center. Contrary to initial expectations that injection would trip the boundary layer flow into the turbulent regime, the results indicated that the high free stream acceleration apparently kept the flow laminar for holes in the first 45 degrees past stagnation. The trend in Stanton number reduction due to coolant injection was predicted with generally good agreement at the lower blowing rates, but for multiple rows of holes, agreement was poor beyond the first row.

Copyright © 1983 by ASME
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