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<p>Brush seals in gas turbine engines offer effective sealing performance but may encounter instability at high swirl velocities, potentially leading to seal failure. This investigation employs fluid-structure interaction (FSI) analysis to examine the deformation of bristle packs under swirling flow conditions and evaluates the influence of geometric parameters through a design of experiments (DOE) methodology. The critical parameters encompass the bristle diameter, length, inclined angle, number of rows, radial clearance, and spacing between bristles. The findings of this study indicate that circumferential slip, associated with the normal-to-axial force ratio on the bristle pack, precipitates instability at elevated ratios. The spacing between the bristles and their inclination angle substantially affect the aerodynamic force ratio, with contributions of 26.5 % and 23.6 %, respectively. Radial clearance emerges as the predominant factor influencing leakage, explaining 74 % of its variability, with leakage increasing linearly with radial clearance. Structural optimization of the brush seal enhances aerodynamic stability and achieves a reduction in leakage of approximately 90 %.</p>

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Fluid-structure interaction analysis of sensitive factors for circumferential slip instability of brush seals in gas turbine engines

  • 期刊论文

  • 发表日期：

    2025年3月3日

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  • Yuxin Liu,
  • Benzhuang Yue,
  • Xiaozhi Kong,
  • Peng Zhu

摘要

Brush seals in gas turbine engines offer effective sealing performance but may encounter instability at high swirl velocities, potentially leading to seal failure. This investigation employs fluid-structure interaction (FSI) analysis to examine the deformation of bristle packs under swirling flow conditions and evaluates the influence of geometric parameters through a design of experiments (DOE) methodology. The critical parameters encompass the bristle diameter, length, inclined angle, number of rows, radial clearance, and spacing between bristles. The findings of this study indicate that circumferential slip, associated with the normal-to-axial force ratio on the bristle pack, precipitates instability at elevated ratios. The spacing between the bristles and their inclination angle substantially affect the aerodynamic force ratio, with contributions of 26.5 % and 23.6 %, respectively. Radial clearance emerges as the predominant factor influencing leakage, explaining 74 % of its variability, with leakage increasing linearly with radial clearance. Structural optimization of the brush seal enhances aerodynamic stability and achieves a reduction in leakage of approximately 90 %.