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A Pressure Gradient Sensitive Wall Function for the Prediction of Turbulent Flow in Thermal Turbomachinery

[+] Author Affiliations
Paul Pieringer, Wolfgang Sanz

Graz University of Technology, Graz, Austria

Paper No. GT2005-68471, pp. 1089-1098; 10 pages
doi:10.1115/GT2005-68471
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

The economical design of thermal turbine stages of high efficiency requires very fast CFD tools of high accuracy. Since efficiency is mainly determined by secondary flow, a major focus in CFD is laid on boundary layer treatment. By resolving the boundary layer using a fine grid, usually the best results can be achieved, but at cost of computational time and memory. Wherever resolving the boundary layer is unacceptable, wall functions are used for simulating the flow close to solid walls. This paper describes a novel wall function approach for the prediction of three-dimensional turbulent boundary layer flows. The model is designed especially for the application to thermal turbomachinery in order to properly predict accelerated, decelerated and separated boundary layers at transonic conditions. The model is based on the law-of-the-wall expression by Spalding and also considers the shear-stress distribution perpendicular to the wall surface, which is mainly determined by pressure gradients. To cope with the boundary conditions, this wall function model uses phantom (ghost) cells, that must be located within the boundary layer, so there is a clearance between the first calculation cell and the wall. This allows an improved grid resolution for wall function approaches. To verify the accuracy of the model, results are shown for turbomachinery vane test cases at both steady state and time-resolved flow conditions.

Copyright © 2005 by ASME

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