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Numerical Investigations of Geometric Design Parameters Defining Nozzle Guide Vane Endwall Heat Transfer

[+] Author Affiliations
Frank G. Rubensdörffer

Siemens Industrial Turbomachinery AB, Finspong, Sweden

Torsten H. Fransson

Royal Institute of Technology, Stockholm, Sweden

Paper No. GT2006-90177, pp. 173-182; 10 pages
doi:10.1115/GT2006-90177
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

The objective of this work is to compare the predicted flow field and the endwall heat transfer of a baseline nozzle guide vane configuration with a combustion chamber variant, a heat shield variant without and with additional cooling air, and a cavity variant without and with additional cooling air. The comparison is carried out numerically using the commercial 3D Navier-Stokes software package Fluent [1]. For the turbulence modeling the v2 -f model by Durbin [2] been used. The detailed comparison of the flow field and the endwall heat transfer shows major differences between the baseline and heat shield configuration. The heat shield in front of the airfoil of the nozzle guide vane cascade influences the secondary flow field and the endwall heat transfer pattern strongly. The additional cooling air, released under the heat shield also has a distinctive influence. The cavity between the combustion chamber and the nozzle guide vane affects the secondary flow field and the endwall heat transfer pattern. Here the influence of the additional cavity cooling air is more decisive.

Copyright © 2006 by ASME

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