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Temperature-Based Optimization of Film Cooling in Gas Turbine Hot Gas Path Components

[+] Author Affiliations
Felipe A. C. Viana, Jack Madelone, Niranjan Pai, Genghis Khan, Sanghum Baik

GE Global Research, Niskayuna, NY

Paper No. GT2013-94293, pp. V03CT18A001; 6 pages
doi:10.1115/GT2013-94293
From:
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 3C: Heat Transfer
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5516-4
  • Copyright © 2013 by ASME

abstract

To achieve high efficiency, modern gas turbines operate at temperatures that exceed melting points of metal alloys used in turbine hot gas path parts. Parts exposed to hot gas are actively cooled with a portion of the compressor discharge air (e.g., through film cooling) to keep the metal temperature at levels needed to meet durability requirements. However, to preserve efficiency, it is important to optimize the cooling system to use the least amount of cooling flow. In this study, film cooling optimization is achieved by varying cooling hole diameters, hole to hole spacing, and film row placements so that the specified targets for maximum metal temperature are met while preserving (or saving) cooling flow. The computational cost of the high-fidelity physics models, the large number of design variables, the large number and nonlinearity of responses impose severe challenges to numerical optimization. Design of experiments and cheap-to-evaluate approximations (radial basis functions) are used to alleviate the computational burden. Then, the goal attainment method is used for optimizing of film cooling configuration. The results for a turbine blade design show significant improvements in temperature distribution while maintaining/reducing the amount of used cooling flow.

Copyright © 2013 by ASME

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