A Combined Experimental and Theoretical Study of Flow and Pressure Distributions in a Brush Seal

Bayley, F. J.; Long, Chris A.

doi:10.1115/1.2906723

Cited by 64 publications

(27 citation statements)

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“…The leakage rate of brush seals showed a slight decrease at rotating condition. Bayley and Long 4 first measured and published the axial and radial pressure distributions under the bristle tips and along the backing plate of brush seal using a non-rotating test rig. They concluded that the contact pressure between the bristle pack and rotor surface increases linearly with respect to pressure ratio.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The airflow goes through the porous bristle pack is subject to additional resistance forces. Bayley and Long 4 first introduced the linear Darcian porous medium model only considered the viscous flow resistance to predict the leakage flow of interference brush seal. Chew et al.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The reliability of the porosity and resistance coefficients of the bristle pack had been validated by comparing the numerical results with the experimental leakage rates and pressure distributions of Bayley and Long. 4 The details of the validation were presented in authors’ previous article. 15…”

Section: Numerical Approachmentioning

confidence: 99%

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Investigation into the flow behavior of multi-stage brush seals

Qiu

Yan

2014

Proceedings of the Institution of Mechanical Engineers, Part A:

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Brush seals have found increasing use in turbomachinery within the past decade due to their superior sealing performance and flexible nature. The flow characteristics and fundamental behavior of single brush seal are known. However, the flow behavior of multi-stage brush seal combined with labyrinth teeth still requires further research. This article presents a detailed investigation into flow behavior of multi-stage brush seal combined with labyrinth teeth for turbine applications. The leakage rate through a two-stage brush seal combined with labyrinth teeth was measured using the rotating test rig at three operating clearances and four rotational speeds. The leakage rate through the seal was also numerically predicted using Reynolds-averaged Navier–Stokes solutions coupled with non-Darcian porous medium approach. To predict the seal leakage more accurately, the clearance reduction resulted from rotor centrifugal growth was considered in brush seal flow calculations. The effects of rotational speeds and sealing clearance on the leakage performance of the two-stage brush seal were evaluated based on the experimental and numerical results. In addition, to obtain an insight into flow mechanisms of multi-stage brush seals, the leakage rate, flow field, pressure distribution of bristle pack, and aerodynamic force acting on bristle pack of four different types of multi-stage brush seals were also analyzed and compared.

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Section: Literature Reviewmentioning

confidence: 99%

Section: Literature Reviewmentioning

confidence: 99%

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Investigation into the flow behavior of multi-stage brush seals

Qiu

Yan

2014

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…To widen the brush seal application in turbomachinery industry, many experimental tests and numerical models have been developed to investigate the sealing mechanisms of brush seals. Bayley and Long 13 experimentally and numerically analyzed the leakage flow and pressure distribution of typical brush seal earlier. The much smaller leakage flow rate of the zero clearance contacting brush seal was demonstrated.…”

Section: Introductionmentioning

confidence: 99%

“…The numerical leakage flow rate and pressure distribution were in well agreement with the experimental data. 13 The bristle pack was dealt with the porous medium and gradually used to investigate the leakage flow of brush seal. 17 Qiu et al.…”

Section: Introductionmentioning

confidence: 99%

Application of blade tip shroud brush seal to improve the aerodynamic performance of turbine stage

Zhang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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The blade tip shroud brush seal is applied to replace the labyrinth seal for the aerodynamic performance improvement of turbine stage. The leakage flow characteristics of the brush seal are numerically predicted by using the Reynolds-Averaged Navier–Stokes equations and non-linear Darcian porous medium model. The numerical leakage flow rate of the brush seal is in well agreement with the experimental data. The last and first long teeth of the labyrinth seal were designed to bristle pack named as the postposed and preposed brush seals based on the 1.5 turbine stage. The leakage flow rate and aerodynamic performance of the turbine stage with blade tip shroud labyrinth seal and brush seal are numerically investigated. The effect of the sealing clearance between bristle pack and tip shroud on the aerodynamic performance of turbine stage is conducted which ranged from 0 mm to 0.4 mm. The axial deflection of the bristle pack is analyzed with consideration of the aerodynamic forces and contact frictional force. The obtained results show that the leakage flow rate of the tip shroud brush seals with bristle tip 0.4 mm clearance which decreases by up to 18% in comparison with the labyrinth seal, and the aerodynamic efficiency increases by 0.6%. Compared to the tip labyrinth seal, tip shroud brush seals can decrease the relative deflection angle of exit flow. This flow behavior results in reducing the mixing loss between the tip leakage flow and mainstream. The similar axial deflection of the bristle pack for two kinds of brush seals is observed at the same sealing clearance. The deflection of the bristle pack under the function of the aerodynamic forces is protected by the backing plate. This work provides the theoretical basis and technical support for the brush seal application in the turbine industries.

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