Enhancement of Film Cooling Effectiveness Using Dean Vortices

Pingting Chen, Lang Wang, Xueying Li, Jing Ren, Hongde Jiang, Terrence Simon

Research output: Contribution to journalArticlepeer-review

Abstract

Film cooling technology is widely used in gas turbines. With the additive manufacturing anticipated in the future, there will be more freedom in film cooling hole design. Exploiting this freedom, the present authors tried using curved holes to generate Dean vortices within the delivery line. These vortices have opposite direction of rotation to the vorticity of the kidney vortices and, thus, there is interaction between these vortices in the mixing region. It is shown that as a result of the inclusion of Dean vortices, the curved hole delivery leads to enhanced film cooling effectiveness. Numerical results, including film cooling effectiveness values, tracking of vortices in the flow field, heat transfer coefficients, and net heat flux reduction (NHFR), are compared between the curved hole, round hole, and a laidback, fan-shaped hole with blowing ratios, M, of 0.5, 1.0, 1.5, 2.0, and 2.5. The comparison shows that film cooling effectiveness values with the curved hole are higher than those with cylindrical film cooling holes at every blowing ratio studied. The curved hole has lower film cooling effectiveness values than the laidback, fan-shaped holes when M = 0.5 and 1.0, but shows advantages when the blowing ratio is higher than 1.0. There is heat transfer enhancement for the curved hole case due to a higher kinetic energy transferred to the near-wall region, however. Nevertheless, the curved hole still displays a higher NHFR when the blowing ratio is high.

Original languageEnglish (US)
Article number011005
JournalJournal of Turbomachinery
Volume142
Issue number1
DOIs
StatePublished - Jan 1 2020

Bibliographical note

Funding Information:
The authors would like to acknowledge the support by the National Natural Science Foundation of China (Project No. 51706116; Funder ID: 10.13039/501100001809), the Science Fund for Creative Research Groups of the National Natural Science Foundation of China (Project No. 51621062; Funder ID: 10.13039/501100001809), Minnesota Supercomputing Institute (MSI) for providing the computational resources for this study and the support provided by China Scholarship Council (Grant No. 201706210252; Funder ID: 10.13039/501100004543) for Pingting Chen to visit the University of Minnesota.

Publisher Copyright:
© 2020 by ASME.

Keywords

  • computational fluid dynamics (CFD)
  • Dean vortices
  • Film cooling
  • gas turbine
  • heat transfer
  • heat transfer and film cooling

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