Surface Heat Transfer From a Three-Pass Blade Cooling Passage Simulator FREE

[+] Author Affiliations
M. K. Chyu, V. Natarajan

Carnegie Mellon University, Pittsburgh, PA

Paper No. 94-GT-164, pp. V004T09A019; 9 pages
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7886-6
  • Copyright © 1994 by ASME


Using an analog mass transfer system based on naphthalene sublimation, the present research focuses on investigating the local heat transfer characteristics from three-pass smooth and turbulated blade cooling passages. To simulate the actual passage geometry, the test model is incorporated with trapezoidal cross-sections including variable passage sizes. Measured local mass transfer results reveal strong evidence of velocity re-distribution over the trapezoidal flow area. Elevated mass transfer always exists in the vicinity of a sharp turn. However, in the present study, one of the most notable mass transfer increases is perceived in the third pass, downstream to the second turn, where the flow area is reduced severely. Overall, the combined effects of the three-pass and two sharp turns virtually doubles the mass transfer as compared to its straight counterpart with fully developed, turbulent flow. With a pitch-to-height ratio equal to 10 and 90-degree orientation, the rib turbulators produce approximately an additional 30% of overall mass transfer enhancement in comparison to the smooth case. Locally, rib-induced enhancement varies with different surfaces and passes. The greatest enhancement lies on the first pass, about 40%; the other two passes are comparable, less than 20%.

Copyright © 1994 by ASME
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