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Experimental and Numerical Investigation of Effusion Cooling for High Pressure Turbine Components: Part 2 — Numerical Results

[+] Author Affiliations
Gustavo A. Ledezma, Julienne Lachance, Guanghua Wang

GE Global Research Center, Niskayuna, NY

Anquan Wang, Gregory M. Laskowski

GE Aviation, Cincinnati, OH

Paper No. GT2016-56400, pp. V05BT17A002; 9 pages
doi:10.1115/GT2016-56400
From:
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 5B: Heat Transfer
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4979-8
  • Copyright © 2016 by ASME

abstract

In this study, numerical simulations of adiabatic film cooling effectiveness are carried out on a round hole effusion cooling flat plate configuration. The numerical method used was a Large Eddy Simulation (LES) with periodic unstructured hexa-dominant grids. The numerical 2-D surface effectiveness and the laterally-averaged effectiveness are compared against the Pressure Sensitive Paint (PSP) results obtained in Part 1 of this paper. The numerical runs were done for a constant gas path Mach (Ma) number of 0.1 and 3 film blowing ratios in the 0.6–1.0 range. The objective is to demonstrate the ability of the LES method to capture the physics of η over a relevant range of blowing ratios. The LES predictions of laterally-averaged and local film effectiveness show tremendous improvement with respect to steady state Reynolds Averaged Navier Stokes (RANS) model results. Furthermore the LES data agrees very well with the experimental data.

Copyright © 2016 by ASME

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