RESEARCH PAPERS: Gas Turbines: Heat Transfer

Experimental Investigation and Mathematical Modeling of Clearance Brush Seals

[+] Author and Article Information
M. T. Turner

Propulsion Systems Integration, Rolls-Royce, P.O. Box 3, Filton, Bristol, BS12 7QE, United Kingdom

J. W. Chew

Mechanical Science Group, Rolls-Royce, Moor Lane, Derby, DE24 8BJ, United Kingdom

C. A. Long

Thermo-Fluid Mechanics Research Centre, University of Sussex, Brighton, Sussex, BN1 9QT, United Kingdom

J. Eng. Gas Turbines Power 120(3), 573-579 (Jul 01, 1998) (7 pages) doi:10.1115/1.2818185 History: Received March 15, 1997; Online November 19, 2007


In this paper, an experimental program and a CFD based mathematical model using a brush seal at two bristle to rotor clearances (0.27 mm and 0.75 mm) are presented. The experimental program examined the radial pressure distributions along the backing ring, the axial pressure distribution along the rotor, and the mass flow through the seal through a range of pressure ratios while exhausting to atmosphere. The results from this experimental program have been used to further calibrate a CFD-based model. This model treats the bristle pack as an axisymmetric, anisotropic porous region, and is calibrated by the definition of nonlinear resistance coefficients in three orthogonal directions. The CFD analysis calculates the aerodynamic forces on the bristles, which are subsequently used in a separate program to estimate the bristle movements, stresses, and bristle and rotor loads. The analysis shows that a brush seal with a build clearance produces a very different flow field within the bristle pack to one with an interference, and the need to understand the bulk movements of the bristles. These are shown to be affected by the level of friction between the bristles and the backing ring, which has an important effect on the bristles wear and seal leakage characteristics.

Copyright © 1998 by The American Society of Mechanical Engineers
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