Film cooling effectiveness of an advanced-louver cooling scheme for gas turbines

X. Z. Zhang, I. Hassan

Research output: Contribution to journalArticle

59 Citations (Scopus)


A novel film-cooling scheme for high temperature gas turbine applications was introduced in this paper. Compared with the traditional circular hole, the new scheme combines both the advantages of traditional film cooling with those of impingement cooling. The hole that transports coolant fluid from the inside to the outside of the blade is designed in such a way that the coolant must go through a bend before exiting the blade, thus impinging on the blade material. This scheme is expected to produce the greatest coverage on the blade with the least amount of mixing and least possible amount of coolant A benchmark case of a traditional circular hole in a crossflow, the fundamental problem of film cooling, was employed to validate the present methodology with the jet liftoff effect clearly captured in the simulation. Turbulence was modeled using four different turbulence models, namely, k-ε (including its three variants), k-ω, Reynolds-stress, and Spalart-Alhnaras with different wall treatments. It was found that the proposed cooling scheme can prevent the jets from penetrating into the mainstream much better and provide more uniform protection on the surface, indicating that the proposed scheme yields superior performance.

Original languageEnglish
Pages (from-to)754-763
Number of pages10
JournalJournal of Thermophysics and Heat Transfer
Issue number4
Publication statusPublished - 1 Oct 2006
Externally publishedYes


ASJC Scopus subject areas

  • Condensed Matter Physics
  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Space and Planetary Science

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