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静态篦齿封严温变效应产生机理数值研究

李昶威 孙丹 赵欢 王泽铭 张然

李昶威, 孙丹, 赵欢, 等. 静态篦齿封严温变效应产生机理数值研究[J]. 航空动力学报, 2024, 39(2):20220219 doi: 10.13224/j.cnki.jasp.20220219
引用本文: 李昶威, 孙丹, 赵欢, 等. 静态篦齿封严温变效应产生机理数值研究[J]. 航空动力学报, 2024, 39(2):20220219 doi: 10.13224/j.cnki.jasp.20220219
LI Changwei, SUN Dan, ZHAO Huan, et al. Numerical study on the generation mechanism of temperature variation effect of static labyrinth seals[J]. Journal of Aerospace Power, 2024, 39(2):20220219 doi: 10.13224/j.cnki.jasp.20220219
Citation: LI Changwei, SUN Dan, ZHAO Huan, et al. Numerical study on the generation mechanism of temperature variation effect of static labyrinth seals[J]. Journal of Aerospace Power, 2024, 39(2):20220219 doi: 10.13224/j.cnki.jasp.20220219

静态篦齿封严温变效应产生机理数值研究

doi: 10.13224/j.cnki.jasp.20220219
基金项目: 国家自然科学基金(52075346,51675351); 先进航空动力创新工作站(依托中国航空发动机研究院设立)项目(HKC2020-02-030)
详细信息
    作者简介:

    李昶威(1999-),男,硕士生,主要从事篦齿封严温变效应研究

    通讯作者:

    孙丹(1981-),男,教授,博士,主要从事透平机械先进密封技术研究。E-mail:phd_sundan@163.com

  • 中图分类号: V23

Numerical study on the generation mechanism of temperature variation effect of static labyrinth seals

  • 摘要:

    采用理论分析和数值计算的方法系统地研究了静态篦齿封严温变效应产生机理和影响因素,对静态篦齿封严温变效应进行了理论分析,建立了基于RNG(renormalization group) k-ε湍流方程的数值求解模型。研究了静态篦齿封严温变效应,分析了压比和相对封严间隙对温变效应的影响规律,揭示了静态篦齿封严温变效应产生机理。结果表明:气体流经封严间隙温度先降低后升高,从涡流中心到外缘温度升高,齿腔近壁面气体温度升高。篦齿封严局部气体温度既有升高也有降低,总体上温度沿轴向降低;静态篦齿封严气体温度随压比和相对封严间隙的增加而降低,当压比为1.6,相对封严间隙为1.6时,温降最多为4.70 K;静态篦齿封严的温变效应主要是由其节流效应、热力学效应和摩擦效应产生。气体在间隙由于节流效应,分子动能减小,在齿腔由于热力学效应,涡流中心动能传递给涡流外缘,在齿腔近壁面由于摩擦效应,气体动能转换为热能。研究成果为篦齿封严间隙气流热分析提供了理论依据。

     

  • 图 1  篦齿封严温变效应产生机理图

    Figure 1.  Mechanism of temperature variation effect of labyrinth seals

    图 2  静态篦齿封严结构示意图

    Figure 2.  Schematic diagram of static labyrinth seals structure

    图 3  网格划分

    Figure 3.  Grid generation method

    图 4  网格节点数对泄漏量的影响

    Figure 4.  Influences of number of grid nodes on leakage

    图 5  准确性验证模型总温云图

    Figure 5.  Total temperature contour of accuracy verification model

    图 6  节流过程气流温度变化

    Figure 6.  Temperature variation of airflow during throttling

    图 7  涡流和近壁面气流温度变化

    Figure 7.  Temperature variation of airflow in swirl and near wall

    图 8  静态篦齿封严泄漏流的总温云图(s/b=0.8)

    Figure 8.  Total temperature contour of static labyrinth seals (s/b= 0.8)

    图 9  静态篦齿封严泄漏流的总温云图(π=1.6)

    Figure 9.  Total temperature contour of static labyrinth seals (π=1.6)

    图 10  静态篦齿封严速度矢量图

    Figure 10.  Velocity vectors of static labyrinth seals

    图 11  静态篦齿封严轴向总压分布

    Figure 11.  Distribution of axial total pressure of static labyrinth seals

    图 12  静态篦齿封严气流轴向温度随压比的变化

    Figure 12.  Variation of axial temperature of static labyrinth seals airflow with pressure ratio

    图 13  静态篦齿封严气流轴向温度随相对封严间隙的变化

    Figure 13.  Variation of axial temperature of static labyrinth seals airflow with relative seal clearances

    图 14  压比和相对封严间隙对温变效应的影响机理

    Figure 14.  Influence mechanism of pressure ratio and relative seal clearances on temperature variation effect

    图 15  节流过程参数变化

    Figure 15.  Throttling process parameter changes

    图 16  涡流效应能量传递

    Figure 16.  Swirl effect energy transfer

    图 17  壁面附近速度分布示意图

    Figure 17.  Schematic diagram of velocity distribution near the wall

    表  1  静态篦齿封严结构尺寸

    Table  1.   Static labyrinth seals structure size mm

    结构参数数值
    进口下壁面半径147.30
    出口下壁面半径148.80
    齿高3.20
    齿腔底部半径150.00
    上壁面半径153.55
    齿尖厚度0.30
    齿距3.00
    下载: 导出CSV

    表  2  静态篦齿封严边界条件

    Table  2.   Boundary conditions of static labyrinth seals

    边界条件数值
    压比1.2~2.0
    进口温度/K300.0
    下载: 导出CSV

    表  3  不同方法计算的篦齿封严泄漏量和风阻温升值

    Table  3.   Labyrinth seals leakage and windage heating calculated by different methods

    参数本文CFD文献[22]相对误差/%
    泄漏量/(g/s)9.509.691.96
    风阻温升/K7.897.850.51
    下载: 导出CSV
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  • 收稿日期:  2022-04-16
  • 网络出版日期:  2023-07-05

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