Journal of Mechanical Science and Technology

, Volume 24, Issue 10, pp 2035–2042 | Cite as

Performance assessment limits in transonic 3D turbine stage blade rows using a mixing-plane approach

  • José C. PáscoaEmail author
  • Carlos Xisto
  • Emil Göttlich


Numerical computation of gas turbine flowfields demands high computing power. In the present work, we present a detailed analysis of 3D computations for a highly loaded transonic blade and for a gas turbine stage. Comparison between experimental results and numerical computations reveals the precision limits of current modeling assumptions. Computations are performed using a time-marching approach coupled with a mixing-plane model for the exchange of flowfields between stator and rotor domains. Eddy viscosity turbulence models are applied to compute the flow with and without wall functions. Limitations in performance assessment are presented regarding the level of detail used for the geometry definition, the mixing-plane approach, and the near wall turbulence model employed.


Turbulence model Turbine stage Mixing-plane Transonic flow 


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Copyright information

© The Korean Society of Mechanical Engineers and Springer-Verlag Berlin Heidelberg 2010

Authors and Affiliations

  • José C. Páscoa
    • 1
    Email author
  • Carlos Xisto
    • 1
  • Emil Göttlich
    • 2
  1. 1.Faculty of EngineeringUniversity of Beira InteriorCovilhãPortugal
  2. 2.Institute for Thermal Turbomachinery and Machine DynamicsGraz University of TechnologyGraz, StyriaAustria

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