Abstract

Bristles in the first few rows float up from the rotor surface due to the radial airflow in the gap between the front plate and bristle pack, which directly affects seal performance and the service life of a brush seal. In this paper, firstly, two three-dimensional transient calculation models for a traditional brush seal (TBS) and a brush seal with disturbance-suppressing holes (DSBS) are established, respectively, based on the arbitrary Lagrange–Eulerian (ALE) method to study bristle deformation characteristics and leakage flow characteristics of the seals. Furthermore, effects of disturbance-suppressing (DS) hole structural parameters (i.e., height, diameter, and number of hole rows) were investigated to reveal the suppression mechanism of the DS holes on the buoyancy effect of bristles. The results showed that as soon as free ends of bristles at the first few rows moved along direction of the front plate in response to the radial airflow from the gap between front plate and bristle pack, a buoyancy effect of bristles occurred. The DSBS with DS holes set in the front plate of the TBS had a lower deformation of the bristles and a lower leakage amount of seal compared with that of TBS, indicating a good suppression to the buoyancy effect. With decreasing hole height and increasing hole diameter and number of hole rows, the suppression of bristle disturbance gradually increased due to decreases of the radial airflow and increases of torque acting on the bristles.

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Data Availability Statement

Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.

Acknowledgments

The authors wish to thank the support of National Natural Science Foundation of China (52075346), Liaoning Revitalization Talents Program (XLYC2007077), Research Project of Liaoning Provincial Department of Education (LJKZ0179), and Industry-University-Research Cooperation Project of China Aeroengine Group (HFZL2021CXY012).

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Go to Journal of Aerospace Engineering
Journal of Aerospace Engineering
Volume 37Issue 6November 2024

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Received: Jul 17, 2023
Accepted: May 1, 2024
Published online: Jul 30, 2024
Published in print: Nov 1, 2024
Discussion open until: Dec 30, 2024

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Professor, Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China. Email: [email protected]
JiSheng Sun [email protected]
Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China. Email: [email protected]
Professor, Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China (corresponding author). Email: [email protected]
Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China. ORCID: https://orcid.org/0000-0002-9865-2140. Email: [email protected]
Haoyu Yin, Ph.D. [email protected]
Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China. Email: [email protected]
Wen-feng Xu, Ph.D. [email protected]
Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System, Shenyang Aerospace Univ., Shenyang 110136, China. Email: [email protected]

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