Energy separation in high subsonic turbine cascade

Mahmoud M. El-Gend, Mohammed K. Ibrahim, Koichi Mor, Yoshiaki Nakamura

Research output: Contribution to journalReview articlepeer-review

5 Citations (Scopus)


Trailing edge vortex shedding from a turbine cascade was numerically simulated for an exit isentropic Mach number of 0.79 and a Reynolds number of 2:8 × 106. The objective of this study is to clarify the time evolution of the vortex shedding process from a turbine blade and the mechanism of energy separation appearing in the wake. Calculations used a locally developed numerical code, employing a second-order AUSM scheme for inviscid numerical fluxes, a second order implicit dual time method for time integration, and Detached Eddy Simulation for turbulence. Calculated results confirmed a non-uniform pressure distribution along the trailing edge, which was observed experimentally and different from a uniform distribution at low subsonic Mach number. The energy separation where instantaneous total temperature splits into hot and cold spots in the wake is caused by convection and vortex rotation. In addition, the formation and dissipation phases of vortices affect the energy separation.

Original languageEnglish
Pages (from-to)206-212
Number of pages7
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Issue number178
Publication statusPublished - 2009
Externally publishedYes


  • CFD
  • Compressible flows
  • Turbine flows
  • Vortex shedding
  • Wake

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science


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