留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

叶尖定时测量误差的高精度实验分析与修正

蒙一鸣 肖志成 欧阳华

蒙一鸣, 肖志成, 欧阳华. 叶尖定时测量误差的高精度实验分析与修正[J]. 航空动力学报, 2024, 39(7):20220475 doi: 10.13224/j.cnki.jasp.20220475
引用本文: 蒙一鸣, 肖志成, 欧阳华. 叶尖定时测量误差的高精度实验分析与修正[J]. 航空动力学报, 2024, 39(7):20220475 doi: 10.13224/j.cnki.jasp.20220475
MENG Yiming, XIAO Zhicheng, OUYANG Hua. High-accuracy experimental analysis and correction of blade tip timing measurement error[J]. Journal of Aerospace Power, 2024, 39(7):20220475 doi: 10.13224/j.cnki.jasp.20220475
Citation: MENG Yiming, XIAO Zhicheng, OUYANG Hua. High-accuracy experimental analysis and correction of blade tip timing measurement error[J]. Journal of Aerospace Power, 2024, 39(7):20220475 doi: 10.13224/j.cnki.jasp.20220475

叶尖定时测量误差的高精度实验分析与修正

doi: 10.13224/j.cnki.jasp.20220475
基金项目: 国家科技重大专项(J2019-Ⅱ-0005-0025); 中国联合重燃专项(19UGTC037)
详细信息
    作者简介:

    蒙一鸣(1998-),男,硕士生,主要从事叶轮机械振动测试相关研究

    通讯作者:

    欧阳华(1973-) 男,研究员、博士生导师,博士,主要从事航空发动机气动声学及风扇/压气机气动弹性相关研究。E-mail:oyh@sjtu.edu.cn

  • 中图分类号: V19

High-accuracy experimental analysis and correction of blade tip timing measurement error

  • 摘要:

    叶顶位移的精确测量是叶尖定时(BTT)技术应用于旋转叶片振动模态重构和实时状态监测的基础。设计了一套基于激光位移传感器的高精度BTT标定装置,在实验中直接获取叶顶位移的时域标定数据,并以此确定了转速波动是叶顶位移测量误差的主要来源之一。在此基础上,提出了局部5阶拟合的转速波动修正方法以提升BTT测量精度,并在标定装置上完成实验验证。结果表明:局部5阶拟合的转速波动修正方法在不同工况下均能有效提高BTT测量准确度。在旋转叶片非线性升转状态下测量误差最高降低90%;在恒定转速条件下误差可以降低38%至63%。将该算法应用在一台单级轴流压气机的实验数据中,修正的误差达0.4 mm,有效降低了BTT技术实时测量叶顶位移量的不确定度。

     

  • 图 1  叶顶位移测量示意图

    Figure 1.  Schematic diagram of blade tip deflection measurement

    图 2  BTT标定实验装置

    Figure 2.  Calibration test bench of BTT

    图 3  悬臂径向位移仿真结果

    Figure 3.  Cantilever radial displacement simulation results

    图 4  叶片坎贝尔图

    Figure 4.  Campbell diagram of blades

    图 5  传感器安装位置

    Figure 5.  Sensor installation angle

    图 6  叶顶位移的实际值与测量值

    Figure 6.  Actual and measured value of tip displacement

    图 7  测量值与真值相关系数

    Figure 7.  Correlation coefficient between measurement and true data

    图 8  总误差概率密度分布

    Figure 8.  Probability density distribution of total error

    图 9  总误差与轴位置误差关系

    Figure 9.  Relationship between total error and shaft position error

    图 10  残余误差概率密度分布

    Figure 10.  Probability density distribution of residual error

    图 11  升转状态下的误差与修正结果

    Figure 11.  Error and correction results at increased speed

    图 12  稳定工况下的误差与修正结果

    Figure 12.  Errors and correction results under stable conditions

    图 13  相对误差的标准差与键相标识个数

    Figure 13.  Standard deviation of relative error and number of key-phases

    图 14  稳定工况下误差修正结果

    Figure 14.  Error correction results under stable conditions

    图 15  单级压气机实验台

    Figure 15.  Rotor of single-stage compressor test bench

    图 16  叶片振动位移

    Figure 16.  Blade vibration displacement

    图 17  叶片安装角与相对误差

    Figure 17.  Blade installation angle and relative error

    表  1  实验工况

    Table  1.   Experimental conditions

    工况稳定转速/(r/min)附加激励频率/Hz
    A300
    B600
    C900
    D1200
    E30053.8
    F60054.6
    G90056.1
    H120057.5
    下载: 导出CSV

    表  2  总误差与轴位置误差相关的系数

    Table  2.   Correlation coefficient between total error and shaft position error

    传感器编号安装角度/(°)相关系数
    180.20.9910
    2176.80.9934
    3206.70.9936
    4249.50.9896
    5273.90.9916
    6302.70.9825
    7336.50.9829
    下载: 导出CSV
  • [1] CHEN Zhongsheng,SHENG Hao,XIA Yemei,et al. A comprehensive review on blade tip timing-based health monitoring: status and future[J]. Mechanical Systems and Signal Processing,2020,149(1): 107330.1-107330.21.
    [2] 高志坤,张成龙,王威,等. 重型燃气轮机压气机第一级转子叶片断裂分析[J]. 航空发动机,2021,47(1): 47-52. doi: 10.13477/j.cnki.aeroengine.2021.01.009

    GAO Zhikun,ZHANG Chenglong,WANG Wei,et al. Fracture analysis of first stage rotor blade of heavy gas turbine compressor[J]. Aeroengine,2021,47(1): 47-52. (in Chinese) doi: 10.13477/j.cnki.aeroengine.2021.01.009
    [3] PRZYSOWA R,RUSSHARD P. Non-contact measurement of blade vibration in an axial compressor[J]. Sensors,2019,20(1): 68. doi: 10.3390/s20010068
    [4] 张帅,张强波,张霞妹. 基于方差分析的航空发动机风扇叶片外物撞击识别[J]. 航空学报,2021,42(5): 187-198.

    ZHANG Shuai,ZHANG Qiangbo,ZHANG Xiamei. Identification of foreign object impact on aero-engine fan blades with variance analysis[J]. Acta Aeronautica et Astronautica Sinica,2021,42(5): 187-198. (in Chinese)
    [5] 王维民,陈子文,张旭龙,等. 基于叶端定时的转子碰摩故障诊断方法[J]. 航空学报,2022,43(8): 36-45.

    WANG Weimin,CHEN Ziwen,ZHANG Xulong,et al. Fault diagnosis method of rotor rub impact based on blade tip timing[J]. Acta Aeronautica et Astronautica Sinica,2022,43(8): 36-45. (in Chinese)
    [6] MOHAMED M,BONELLO P,RUSSHARD P. A novel method for the determination of the change in blade tip timing probe sensing position due to steady movements[J]. Mechanical Systems and Signal Processing,2019,126: 686-710. doi: 10.1016/j.ymssp.2019.02.016
    [7] WANG Weimin,HU Dongfang,LI Qihang,et al. An improved non-contact dynamic stress measurement method for turbomachinery rotating blades based on fundamental mistuning model[J]. Mechanical Systems and Signal Processing,2020,144(1): 106851.1-106851.18.
    [8] CHEN Zhongsheng,HE Jing,ZHAN Chi. Undersampled blade tip-timing vibration reconstruction under rotating speed fluctuation: uniform and nonuniform sensor configurations[J]. Shock and Vibration,2019,2019: 8103216.1-8103216.13.
    [9] RUSSHARD P. Blade tip timing (BTT) uncertainties[R]. AIP Conference Proceedings, 2016, 1740(1): 020003.1-020003.13.
    [10] ZABLOTSKIY I Y,KOROSTELEV Y A. Measurement of turbine blades with the ELURA Device[J]. Energomashinostroneniye,1970,2(1): 36-39.
    [11] HEATH S. A new technique for identifying synchronous resonances using tip-timing[J]. Journal of Engineering for Gas Turbines and Power,2000,122(2): 219-225. doi: 10.1115/1.483198
    [12] HEATH S, SLATER T, MANSFIELD L, et al. Turbomachinery blade tip-timing measurement techniques[R]. Brussels, Belgium: Advisory Group for Aerospace Research and Development Conference: 90th Symposium on Advanced Non-Intrusive Instrumentation for Propulsion Engines, 1997.
    [13] RIGOSI G,BATTIATO G,BERRUTI T M. Synchronous vibration parameters identification by tip timing measurements[J]. Mechanics Research Communications,2017,79: 7-14. doi: 10.1016/j.mechrescom.2016.10.006
    [14] ROBINSON W W, WASHBURN R S. A real time non-interference stress measurement system (NSMS) for determining aero engine blade stresses[C]//Proceedings of the 37th International Instrumentation Symposium. San Diego, US: the Instrumentation Society of America, 1991: 91-103.
    [15] 孙运玺. 基于机匣振动信号的叶片振动分析方法研究[D]. 南京: 南京航空航天大学, 2016.

    SUN Yunxi. Analysis of the blade vibration based on the casing vibration signal[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese)
    [16] CARRINGTON I B,WRIGHT J R,COOPER J E,et al. A comparison of blade tip timing data analysis methods[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering,2001,215(5): 301-312. doi: 10.1243/0954410011533293
    [17] GARRIDO J G,DIMITRIADIS G. Validating blade vibration amplitudes from blade tip-timing data analysis[J]. IMechE,2004,623(23): 205-213.
    [18] DONOHO D L. Compressed sensing[J]. IEEE Transactions on Information Theory,2006,52(4): 1289-1306. doi: 10.1109/TIT.2006.871582
    [19] CANDES E J,WAKIN M B. An introduction to compressive sampling[J]. IEEE Signal Processing Magazine,2008,25(2): 21-30. doi: 10.1109/MSP.2007.914731
    [20] 张智伟,柴鹏飞,孙宗翰,等. 高可靠小条件数压缩感知叶尖定时信号辨识[J]. 航空动力学报,2021,36(3): 509-519. doi: 10.13224/j.cnki.jasp.2021.03.007

    ZHANG Zhiwei,CHAI Pengfei,SUN Zonghan,et al. High reliability identification method of blade tip timing signals based on compressed sensing under small condition number[J]. Journal of Aerospace Power,2021,36(3): 509-519. (in Chinese) doi: 10.13224/j.cnki.jasp.2021.03.007
    [21] RUSSHARD P. Derived once per rev signal generation for Blade Tip Timing systems[C]//IET & ISA 60th International Instrumentation Symposium. London: IET, 2014: 1-5.
    [22] DIAMOND D H,HEYNS P S,OBERHOLSTER A J. Online shaft encoder geometry compensation for arbitrary shaft speed profiles using Bayesian regression[J]. Mechanical Systems and Signal Processing,2016,81: 402-418. doi: 10.1016/j.ymssp.2016.02.060
    [23] ZHOU Changyi, HU Haifeng, GUAN Fengjiao, et al. Modelling and simulation of blade tip timing uncertainty from rotational speed fluctuation[C]//2017 Prognostics and System Health Management Conference. Piscataway, US: IEEE, 2017: 1-5.
    [24] ZHANG Jiwang,ZHANG Laibin,DING Keqin,et al. Blade tip-timing technology with multiple reference phases for online monitoring of high-speed blades under variable-speed operation[J]. Measurement Science Review,2018,18(6): 243-250. doi: 10.1515/msr-2018-0033
    [25] 王维民,任三群,陈立芳,等. 基于键相插值法的叶片振动测量研究[J]. 振动、测试与诊断,2017,37(2): 361-365,409.

    WANG Weimin,REN Sanqun,CHEN Lifang,et al. The blade vibration measurement research based on the key phase interpolation method[J]. Journal of Vibration, Measurement & Diagnosis,2017,37(2): 361-365,409. (in Chinese)
    [26] REN Sanqun,XIANG Xiaorong,ZHAO Wei,et al. An error correction blade tip-timing method to improve the measured accuracy of blade vibration displacement during unstable rotation speed[J]. Mechanical Systems and Signal Processing,2022,162(1): 108030.1-108030.23.
    [27] FAN Zhenfang,LI Hongkun,DONG Jiannan,et al. An improved multiple per revolution-based blade tip timing method and its applications on large-scale compressor blades[J]. Mechanical Systems and Signal Processing,2022,167(1): 108538.1-108538.18.
    [28] BATTIATO G,FIRRONE C M,BERRUTI T M. Forced response of rotating bladed disks: blade tip-timing measurements[J]. Mechanical Systems and Signal Processing,2017,85: 912-926. doi: 10.1016/j.ymssp.2016.09.019
    [29] TAVAKOLPOUR-SALEH A R,SETOODEH A R,GHOLAMZADEH M. A novel multi-component strain-gauge external balance for wind tunnel tests: simulation and experiment[J]. Sensors and Actuators A: Physical,2016,247: 172-186. doi: 10.1016/j.sna.2016.05.035
  • 加载中
图(17) / 表(2)
计量
  • 文章访问数:  58
  • HTML浏览量:  19
  • PDF量:  17
  • 被引次数: 0
出版历程
  • 收稿日期:  2022-07-02
  • 网络出版日期:  2023-10-23

目录

    /

    返回文章
    返回