Investigation on the Rotordynamic Characteristics of Labyrinth Seal with Swirl Brakes

doi:10.7652/xjtuxb202203011

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Investigation on the Rotordynamic Characteristics of Labyrinth Seal with Swirl Brakes

更新时间：2025-07-09

- Investigation on the Rotordynamic Characteristics of Labyrinth Seal with Swirl Brakes
- Vol. 56, Issue 3, Pages: 105-116(2022)
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202203011
  CLC： TK474
- Online First：10 March 2022，
  
  Published：2022
- 稿件说明：
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Investigation on the Rotordynamic Characteristics of Labyrinth Seal with Swirl Brakes[J]. 2022, 56(3): 105-116.
DOI：

Investigation on the Rotordynamic Characteristics of Labyrinth Seal with Swirl Brakes[J]. 2022, 56(3): 105-116. DOI： 10.7652/xjtuxb202203011.

摘要

采用基于转子多频椭圆涡动模型和动网格技术求解非定常RANS方程

研究了高低两种预旋比下具有防旋板结构的迷宫密封气流激振转子动力特性。分析对比了在预旋比分别为0.13和1.32时无防旋板结构迷宫密封(Design 1)、带进口防旋板结构迷宫密封(Design 2)、在Design 2的基础上增加二级防旋板迷宫密封(Design 3)的平均周向速度、泄漏量、转子动力特性系数。数值模拟得到的Design 1的泄漏量和转子动力特性系数与实验数据吻合良好

验证了数值方法的准确性。研究表明:高预旋比会导致Design 1的直接刚度和有效阻尼降低

并使直接阻尼与交叉刚度增加; 预旋比为1.32时Design 2相对于Design 1能明显降低交叉刚度

且降幅达到63.3%～86.3%

Design 3相对于Design 2的交叉刚度降低了12.9%～39.4%; 预旋比0.13时Design 2的交叉刚度小于0

Design 3的交叉刚度绝对值相对于Design 2增加了24.4%～153.0%; Design 2相对于Design 1在预旋比为1.32时有效阻尼项穿越频率从175.1 Hz降低到28.3 Hz

预旋比为0.13时在20 Hz之后的有效阻尼增加31.6%～60.0%; Design 3相对于Design 2在预旋比为1.32时消除了有效阻尼的穿越频率

在预旋比为0.13时有效阻尼增加26.9%～38.0%。在两种预旋比下设计二级防旋板会略微降低直接刚度

减小交叉刚度

增加直接阻尼。本文工作可为增加迷宫密封转子动力特性的防旋板设计提供参考。

Abstract

The airflow excited rotordynamic characteristics of labyrinth seal with swirl brakes at two different inlet preswirl ratios were numerically investigated by solving the unsteady Reynolds-average Navier-Stokes equation based on the multi-frequency elliptical orbit rotor whirling mode and dynamic mesh technique. The average circumferential velocity

leakage flow rate and rotordynamic coefficients of labyrinth seal with inlet swirl brake(Design 2)or double swirl brakes(Design 3)

or without swirl brake(Design 1)

were analyzed at two different inlet preswirl ratios of 0.13 or 1.32. The numerically predicted leakage flow rate and rotordynamic coefficient of experimental labyrinth seal without swirl brake(Design 1)agreed very well with the experimental data

so the accuracy of the used numerical method was validated. The obtained results show that the direct stiffness and the effective damping ofDesign 1 decrease' and the direct damping and cross-coupling stiffness increase' at higher inlet preswirls. The cross-coupling stiffness ofDesign 2 decreases by 63.3%-86.3% compared withDesign 1 at the inlet preswirl ratio of 1.32. The cross-coupling stiffness ofDesign 3 decreases by 12.9%-39.4% compared withDesign 2 at the inlet preswirl ratio of 1.32. The cross-coupling stiffness ofDesign 2 is less than zero at the inlet preswirl ratio of 0.13. The magnitude of negative cross-coupling stiffness ofDesign 3 increases by 24.4%-153.0% compared toDesign 2 at the inlet preswirl ratio of 0.13.Design 2 reduces the crossover frequency of effective damping from 175.1 Hz to 28.3 Hz compared withDesign 1 when the inlet preswirl ratio is 1.32.Design 2 adds 31.5%-60.0% to the effective damping after 20 Hz compared withDesign 1 when the inlet preswirl ratio is 0.13.Design 3 eliminates the crossover frequency of effective damping compared withDesign 2 when the inlet preswirl ratio is 1.32.Design 3 adds 26.9%-38.0% to the effective damping after 20 Hz compared withDesign 1 when the inlet preswirl ratio is 0.13. Adding double swirl brakes inDesign 3 would slightly reduce the direct stiffness and cross-coupling stiffness and increase the direct damping compared withDesign 2 at different inlet preswirl ratio. This research can provide a reference for the swirl brake design to improve rotordynamic characteristics of labyrinth seals.

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references

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丰镇平 1

李志刚 1

李军 1

Related Institution

(Institute of Turbomachinery, Xi'an Jiaotong University,,)

西安交通大学能源与动力工程学院

School of Energy and Power Engineering, Xi'an Jiaotong University

Institute of Turbomachinery, Xi'an Jiaotong University

Nanjing Electric Power Experimental Research Co., Ltd.

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