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The Effect of Combustor-Turbine Interface Gap Leakage on the Endwall Heat Transfer for a Nozzle Guide Vane

[+] Author Affiliations
S. P. Lynch

Virginia Polytechnic Institute and State University, Blacksburg, VA

K. A. Thole

Pennsylvania State University, University Park, PA

Paper No. GT2007-27867, pp. 671-682; 12 pages
doi:10.1115/GT2007-27867
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME

abstract

To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.

Copyright © 2007 by ASME

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