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A Numerical Simulation of a Brush Seal Section and Some Experimental Results PUBLIC ACCESS

[+] Author Affiliations
M. J. Braun, V. V. Kudriavtsev

University of Akron, Akron, OH

Paper No. 93-GT-398, pp. V03CT17A059; 12 pages
doi:10.1115/93-GT-398
From:
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME

abstract

The brush seal technology represents quite a promising advance in the effort of construction of more efficient, and possibly smaller size engines. Conclusions of recent workshops determined that while the brush seals works well, there is a need to improve its performance characteristics. The considerable amount of experimental work performed to date has indicated the importance of the local flow phenomena in the global sealing process performance of the brush (Braun et al., 1990a, 1991b, 1992, Hendricks et al., 1991a). The distributed flow and pressure fields are thus of vital importance for the prediction of the possible sudden failure of the brush seal under unexpected local “pressure hikes”. It is in this context that the authors developed a numerical, two dimensional time dependent formulation of the Navier-Stokes equations with constant properties, and included the effects of inertia, viscous and pressure terms. The algorithm is applied to a set of non-compliant multirow, multicolumn pin configurations that are similar to the ones found in an idealized brush seal configuration. While the numerical parametric investigation aims to establish the occurrence of major flow patterns and associated pressure maps, the experimental portion of the paper is aimed at gaining further insight into the relevant flow structures, and thus guide the development of the mathematical and numerical model.

Copyright © 1993 by ASME
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