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Prediction of Combustor Liner Cooling

[+] Author Affiliations
Jiankun Yuan, Mehmet Dede, Osman Buyukisik

GE Aircraft Engines, Evendale, OH

Yuexi Xiong

GE Global Research Center, Niskayuna, NY

Paper No. GT2006-90269, pp. 249-257; 9 pages
  • 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


Effective cooling of combustor liners is an important and integrated part of jet engine combustor design, as the liner temperature directly impacts the durability of the combustor. Cooling air jet, usually around 1000–1200 °F, is inserted into slots at the onset of each liner panel. These slots and feedholes are together called nuggets. The discrete air jets are expected to coalesce and form a cooling film with uniform velocity at the exit of the slots. This paper presents results of CFD analysis using realizable k–ε turbulence model in a commercial CFD software FLUENT®. For accurate analysis of different nugget feedhole configurations, an appropriately selected turbulent model is crucial for flow and heat transfer analysis. Special care is given to the coefficient of destruction term related to the turbulent decay exponent of the dissipation rate in transport equation. Validation is achieved by comparison of predicted and measured liner cooling film effectiveness from experimental tests conducted under various blowing ratios. Mass transfer analogy method is used to measure cooling film effectiveness, represented by mass fraction of CO2 along combustor liner. Reasonably good agreement is obtained between the CFD analysis results and the experimental data.

Copyright © 2006 by ASME



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