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The Feasibility of Heat Pipe Turbine Vane Cooling FREE

[+] Author Affiliations
Calvin C. Silverstein

CCS Associates, Bethel Park, PA

Joseph M. Gottschlich, Matthew Meininger

Wright Laboratory, Wright-Patterson AFB, OH

Paper No. 94-GT-306, pp. V004T09A046; 7 pages
doi:10.1115/94-GT-306
From:
  • 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

abstract

This paper evaluates the basic feasibility and anticipated benefits to using heat pipe technology to cool the turbine vanes of gas turbine engines.

This concept involves fitting out the vane interior as a heat pipe, extending the vane into an adjacent heat sink and then transferring the vane incident heat through the vane to the heat sink. The baseline is an advanced military fighter engine and the bypass air is the chosen heat sink. The results of this study show a 7.2% increase in engine thrust, a 0.2% decrease in specific fuel consumption with engine weight increased by less than 1% by using this technology.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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