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端封开口角度对挤压油膜阻尼器影响试验

陈亚龙 马会防 黄延忠 张广辉

陈亚龙, 马会防, 黄延忠, 等. 端封开口角度对挤压油膜阻尼器影响试验[J]. 航空动力学报, 2023, 38(11):2629-2638 doi: 10.13224/j.cnki.jasp.20220117
引用本文: 陈亚龙, 马会防, 黄延忠, 等. 端封开口角度对挤压油膜阻尼器影响试验[J]. 航空动力学报, 2023, 38(11):2629-2638 doi: 10.13224/j.cnki.jasp.20220117
CHEN Yalong, MA Huifang, HUANG Yanzhong, et al. Experiment on the effect of piston ring gap angle on the performance of squeeze film damper[J]. Journal of Aerospace Power, 2023, 38(11):2629-2638 doi: 10.13224/j.cnki.jasp.20220117
Citation: CHEN Yalong, MA Huifang, HUANG Yanzhong, et al. Experiment on the effect of piston ring gap angle on the performance of squeeze film damper[J]. Journal of Aerospace Power, 2023, 38(11):2629-2638 doi: 10.13224/j.cnki.jasp.20220117

端封开口角度对挤压油膜阻尼器影响试验

doi: 10.13224/j.cnki.jasp.20220117
详细信息
    作者简介:

    陈亚龙(1985−),男,正高级工程师,硕士,从事航空发动机强度设计与试验工作

  • 中图分类号: V216.2+1;TK14

Experiment on the effect of piston ring gap angle on the performance of squeeze film damper

  • 摘要:

    采用正交激振测试方法,研究了不同供油孔数、不同供油压力与活塞环开口角度对泄漏量的影响,试验识别了挤压油膜阻尼器(SFD)系统的阻尼系数。结果表明:1孔供油且活塞环开口与供油孔重合时泄漏量最大;供油孔数、供油压力与活塞环开口角度共同影响下,低供油压力、1孔供油活塞环开口角度0°时主阻尼系数$ { C_{xx }} $${ C_{yy} } $差异最小;活塞环开口角度0°且最下方的1孔供油时,SFD系统的阻尼性能最好,平均主阻尼系数能达到9.04×104 N·s/m,约为理论短轴承解最大值的5.7倍,建议安装时两个活塞环开口角度为0°以保证具有较好的密封性,提升SFD工作时的减振性能。

     

  • 图 1  SFD动力学系数识别试验装置

    Figure 1.  Dynamic coefficient identification test rig for SFD

    图 2  SFD试验台照片

    Figure 2.  Photo of test rig for SFD

    图 3  滑油在活塞环搭扣处泄漏示意图

    Figure 3.  Schematic of oil leakage at the agraffe of piston ring

    图 4  SFD活塞环端封结构(径向视图)

    Figure 4.  Piston ring end seal structure of SFD (radial view)

    图 5  SFD活塞环端封结构照片

    Figure 5.  Photo of piston ring end seal structure of SFD

    图 6  供油孔、激振力和位移的相对位置

    Figure 6.  Relative position of oil supply hole, shocking force and displacement

    图 7  SFD试验时活塞环开口角度与供油孔相对位置

    Figure 7.  Relative position between the piston ring gap angle and oil supply hole during SFD experiment

    图 8  SFD动力学系数识别示意图

    Figure 8.  Schematic of dynamic coefficient identification for SFD

    图 9  不同活塞环开口角度下频域识别结果

    Figure 9.  Frequency domain identification result of different piston ring gap angles

    图 10  1孔供油时SFD静态与动态泄漏量分析

    Figure 10.  Analysis of static and dynamic leakage of SFD with single oil supply hole

    图 11  3孔供油时SFD静态与动态泄漏量分析

    Figure 11.  Analysis of static and dynamic leakage of SFD with three oil supply holes

    图 12  6孔供油时SFD静态与动态泄漏量分析

    Figure 12.  Analysis of static and dynamic leakage of SFD with six oil supply holes

    图 13  1孔供油时SFD主阻尼系数分析

    Figure 13.  Analysis of SFD principal damping coefficients with single oil supply hole

    图 14  3孔供油时SFD主阻尼系数分析

    Figure 14.  Analysis of SFD principal damping coefficients with three oil supply holes

    图 15  6孔供油时SFD主阻尼系数分析

    Figure 15.  Analysis of SFD principal damping coefficients with six oil supply holes

    图 16  SFD平均主阻尼系数影响

    Figure 16.  Influence of SFD average principal damping coefficient

    表  1  详细试验条件

    Table  1.   Detailed experiment conditions

    参数数值及说明
    等效直径/mm235.2
    油膜半径间隙c/mm0.2$ \pm 0.05 $
    有效油膜长度L/mm25
    滑油牌号15号航空润滑油(地面用)
    滑油动力黏度μ /(mPa·s)3.57(21℃)
    内测活塞环开口角度/(°)0
    外测活塞环开口角度/(°)0, 90, 180, 270
    激振力幅值/N270~370
    激振力频率/Hz52
    供油压力/MPa0.05, 0.1, 0.3, 0.4
    供油孔直径/mm2
    供油孔数1孔—4#供油孔
    3孔—2#、4#、6#供油孔
    6孔—1#~6#供油孔
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-03-07
  • 网络出版日期:  2023-04-11

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