Aerothermal shape optimization for a double row of discrete film cooling holes on the suction surface of a turbine vane

Carole El Ayoubi, Wahid Ghaly, Ibrahim Hassan

Research output: Contribution to journalArticle

7 Citations (Scopus)


A multiple-objective optimization is implemented for a double row of staggered film holes on the suction surface of a turbine vane. The optimization aims to maximize the film cooling performance, which is assessed using the cooling effectiveness, while minimizing the corresponding aerodynamic loss, which is measured with a mass-averaged total pressure coefficient. Three geometric variables defining the hole shape are optimized: the conical expansion angle, compound angle and length to diameter ratio of the non-diffused portion of the hole. The optimization employs a non-dominated sorting genetic algorithm coupled with an artificial neural network to generate the Pareto front. Reynolds-averaged Navier-Stokes simulations are employed to construct the neural network and investigate the aerodynamic and thermal optimum solutions. The optimum designs exhibit improved performance in comparison to the reference design. The optimization methodology allowed investigation into the impact of varying the geometric variables on the cooling effectiveness and the aerodynamic loss.

Original languageEnglish
Pages (from-to)1384-1404
Number of pages21
JournalEngineering Optimization
Issue number10
Publication statusPublished - 3 Oct 2015
Externally publishedYes



  • aerodynamic loss
  • conical expansion
  • cooling effectiveness
  • film cooling
  • optimization

ASJC Scopus subject areas

  • Computer Science Applications
  • Control and Optimization
  • Management Science and Operations Research
  • Industrial and Manufacturing Engineering
  • Applied Mathematics

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