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Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer FREE

[+] Author Affiliations
A. A. Ameri

A.Y.T. Corporation, Brook Park, OH

E. Steinthorsson

NASA Lewis Research Center

Paper No. 96-GT-189, pp. V004T09A018; 8 pages
doi:10.1115/96-GT-189
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7875-0
  • Copyright © 1996 by ASME

abstract

Predictions of the rate of heat transfer to the tip and shroud of a gas turbine rotor blade are presented. The simulations are performed with a multiblock computer code which solves the Reynolds Averaged Navier-Stokes equations. The effect of inlet boundary layer thickness as well as rotation rate on the tip and shroud heat transfer is examined. The predictions of the blade tip and shroud heat transfer are in reasonable agreement with the experimental measurements. Areas of large heat transfer rates are identified and physical reasoning for the phenomena presented.

Copyright © 1996 by ASME
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