Analysis of vibration reduction characteristics and test methods of blisk damping ring
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摘要:
以真实压气机整体叶盘为研究对象，针对整体叶盘3节径各阶模态开展阻尼环减振特性分析。建立了整体叶盘有限元模型。基于整体-局部统一滑动模型，发展了适用于环形阻尼器系统振动响应分析方法，使用该方法对整体叶盘在简谐激励下的振动响应进行仿真计算。设计能够激发整体叶盘节径振动的试验系统，通过试验验证了有限元模型的合理性以及计算方法的有效性。结果表明阻尼环对各阶振型均有很好的减振效果，最高可达60%。试验结果与仿真结果吻合度较好，固有频率相对误差均在5%以内。研究结果对工程上整体叶盘结构减振设计具有一定参考价值。
Abstract:A real compressor blisk was taken as the research object, and the damping ring vibration reduction characteristics were analyzed for three node diameter modes of the blisk. A finite element model of the blisk was established. Based on the global-local unified sliding model, a vibration response analysis method suitable for annular damper system was developed, and the vibration response of a blisk under harmonic excitation was simulated using this method. A test system was designed to excite the pitch diameter vibration of the blisk. The rationality of the finite element model and the effectiveness of the calculation method were verified by tests. The results showed that the damping ring had a good effect on the vibration reduction of various modes, up to 60%. The test results agreed well with the simulation results, and the natural frequency errors were within 5%. The research results have some reference value to the vibration reduction design of the integral bladed disc structure in engineering.
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Key words:
- blisk /
- damping ring /
- vibration reduction test /
- dry friction damping /
- vibration response analysis
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图 13 2 N激振力下幅频特性曲线
Figure 13. Frequency response function curve under2 N excitation force
图 14 5 N激振力下幅频特性曲线
Figure 14. Frequency response function curve under5 N excitation force
图 15 10 N激振力下幅频特性曲线
Figure 15. Frequency response function curve under10 N excitation force
图 16 相对共振峰值随无量纲正压力变化曲线
Figure 16. Relative resonance peak versus dimensionless positive pressure curve
图 26 2 N激振力下幅频特性曲线
Figure 26. Frequency response function curve under2 N excitation force
图 27 5 N激振力下幅频特性曲线
Figure 27. Frequency response function curve under5 N excitation force
图 28 10 N激振力下幅频特性曲线
Figure 28. Frequency response function curve under10 N excitation force
图 29 不同激振力下叶尖相对位移共振峰值随无量纲正压力变化曲线
Figure 29. Relative resonance peak varies with dimensionless positive pressure
表 1 TC17材料参数
Table 1. TC17 material parameters
密度/（kg/m3） 弹性模量/1011 Pa 泊松比 4640 1.115 0.313 
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表 2 整体叶盘第3阶固有频率
Table 2. Third order natural frequencies of monolithic blades
模态阶数 固有频率/Hz 1 309.88 2 1076.4 3 1352.0 4 1479.6 5 2685.9
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表 3 整体叶盘阻尼环减振特性分析结果汇总
Table 3. Summary of analysis results of vibration mitigation characteristics of monolithic blade disk vibration ring
模态阶数 幅值最优减振效果/% 最优无量纲正压力 1 29 10 2 30 6 3 25 30 4 60 10 5 35 12
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表 4 定频试验激励频率范围
Table 4. Constant frequency test excitation frequency range
模态阶数 模态频率/Hz 激励频率范围/Hz 1 308 300～320 2 1100 1090 ～1110 3 1378 1370 ～1385 4 1489 1482 ～1495 5 2572 2550 ～2596
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表 5 整体叶盘阻尼环减振试验结果汇总
Table 5. Summary of results of vibration mitigation tests on the monolithic disk damped ring
模态阶数 幅值最优减振效果/% 最优无量纲正压力 1 45 4～30 2 40 4～25 3 40 10～60 4 43 10～60 5 62 12～60
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表 6 各阶固有频率对比
Table 6. Comparison of natural frequencies of each order
模态阶数 计算结果/Hz 试验结果/Hz 相对误差/% 1 309.88 308 0.61 2 1076.4 1100 2.14 3 1352 1378 1.88 4 1479.6 1489 0.63 5 2685.9 2572 4.42
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表 7 减振效果对比
Table 7. Comparison of vibration mitigation effects
阶次 仿真结果/% 试验结果/% 第1阶 29 45 第2阶 30 40 第3阶 25 40 第4阶 60 43 第5阶 35 62
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表 8 最优正压力结果对比
Table 8. Comparison of optimal positive pressure results
模态阶数 计算最优
无量纲正压力试验最优
无量纲正压力区间1 10 4～30 2 6 4～25 3 30 10～60 4 10 10～60 5 12 12～60
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[1] 王红建,贺尔铭. 叶片失谐对叶盘结构振动特性的影响[J]. 西北工业大学学报,2009,27(5): 645-650. WANG Hongjian,HE Erming. Exploring key features of blade mistuning effects on vibration characteristics of bladed disks[J]. Journal of Northwestern Polytechnical University,2009,27(5): 645-650. (in ChineseWANG Hongjian, HE Erming. Exploring key features of blade mistuning effects on vibration characteristics of bladed disks[J]. Journal of Northwestern Polytechnical University, 2009, 27(5): 645-650. (in Chinese) [2] GRIFFIN J H,HOOSAC T M. Model development and statistical investigation of turbine blade mistuning[J]. Journal of Vibration and Acoustics,1984,106(2): 204-210. doi: 10.1115/1.3269170 [3] IRRETIER H. Coupled vibrations of blades in bending-bending-torsion and disks in out-of-plane and in-plane motion[R]. St. Louis, Mo,US:American Society of Mechanical Engineers,Design Engineering Technical Conference,1979. [4] 叶先磊,王建军,朱梓根,等. 大小叶盘结构连续参数模型和振动模态[J]. 航空动力学报,2005,20(1): 66-72. YE Xianlei,WANG Jianjun,ZHU Zigen,et al. Continuous parameter model and vibration modal of splitter vane rotor[J]. Journal of Aerospace Power,2005,20(1): 66-72. (in ChineseYE Xianlei, WANG Jianjun, ZHU Zigen, et al. Continuous parameter model and vibration modal of splitter vane rotor[J]. Journal of Aerospace Power, 2005, 20(1): 66-72. (in Chinese) [5] 陈玉刚. 整体叶盘振动特性分析与硬涂层阻尼减振设计研究[D]. 大连: 大连理工大学,2017. CHEN Yugang. Analysis of vibration characteristics of integral bladed disk and study on damping and vibration reduction design of hard coating[D]. Dalian: Dalian University of Technology,2017. (in ChineseCHEN Yugang. Analysis of vibration characteristics of integral bladed disk and study on damping and vibration reduction design of hard coating[D]. Dalian: Dalian University of Technology, 2017. (in Chinese) [6] HASSAN M. Vibration analysis of turbomachinery blades[D]. Hartford,Connecticut,US: Faculty of Rensselaer Polytechnic Institute,2008. [7] 王进. 行波激励作用下涂层整体叶盘振动特性测试与分析[D]. 沈阳: 东北大学,2020. WANG Jin. Measurement and analysis of vibration characteristics of coated blisk under traveling wave excitation[D]. Shenyang: Northeastern University,2020. (in ChineseWANG Jin. Measurement and analysis of vibration characteristics of coated blisk under traveling wave excitation[D]. Shenyang: Northeastern University, 2020. (in Chinese) [8] 漆文凯. 涡轮转子叶片叶根阻尼装置减振特性分析及试验研究[D]. 南京: 南京航空航天大学,2005. QI Wenkai. Analysis and experimental study on vibration reduction characteristics of turbine rotor blade root damping device[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2005. (in ChineseQI Wenkai. Analysis and experimental study on vibration reduction characteristics of turbine rotor blade root damping device[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005. (in Chinese) [9] 漆文凯,高德平. 摩擦阻尼减振设计中的局部滑动问题[J]. 航空学报,2006,27(5): 805-809. QI Wenkai,GAO Deping. Microslip study on friction damping and its application in design of vibration reduction[J]. Acta Aeronautica et Astronautica Sinica,2006,27(5): 805-809. (in ChineseQI Wenkai, GAO Deping. Microslip study on friction damping and its application in design of vibration reduction[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(5): 805-809. (in Chinese) [10] 朱永新. 带冠叶片摩擦减振特性研究[D]. 南京: 南京航空航天大学,2007. ZHU Yongxin. Study on friction vibration reduction characteristics of shrouded blades[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2007. (in ChineseZHU Yongxin. Study on friction vibration reduction characteristics of shrouded blades[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2007. (in Chinese) [11] 吴绵绵. 涡轮叶片摩擦阻尼减振设计方法研究[D]. 南京: 南京航空航天大学,2010. WU Mianmian. Study on design method of friction damping vibration reduction of turbine blades[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2010. (in ChineseWU Mianmian. Study on design method of friction damping vibration reduction of turbine blades[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010. (in Chinese) [12] 陈俊杰. 带冠叶盘干摩擦阻尼减振特性研究[D]. 南京: 南京航空航天大学,2015. CHEN Junjie. Study on vibration reduction characteristics of dry friction damping of bladed disk with crown[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2015. (in ChineseCHEN Junjie. Study on vibration reduction characteristics of dry friction damping of bladed disk with crown[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2015. (in Chinese) [13] 温伟,漆文凯. 基于整体叶盘环形摩擦阻尼器减振分析及设计[J]. 航空动力学报,2020,35(4): 777-782. WEN Wei,QI Wenkai. Vibration reduction analysis and design of friction ring damper in blisk[J]. Journal of Aerospace Power,2020,35(4): 777-782. (in ChineseWEN Wei, QI Wenkai. Vibration reduction analysis and design of friction ring damper in blisk[J]. Journal of Aerospace Power, 2020, 35(4): 777-782. (in Chinese) [14] 牛南轲,漆文凯,许正华. 管式减涡器阻尼结构减振特性及设计方法[J]. 航空动力学报,2024,39(6): 20220469. NIU Nanke,QI Wenkai,XU Zhenghua. Damping characteristics and design method of tubular vortex reducer damper[J]. Journal of Aerospace Power,2024,39(6): 20220469. (in ChineseNIU Nanke, QI Wenkai, XU Zhenghua. Damping characteristics and design method of tubular vortex reducer damper[J]. Journal of Aerospace Power, 2024, 39(6): 20220469. (in Chinese) [15] 徐自力,谷伟伟,吕强,等. 基于微动滑移模型的叶片阻尼结构参数研究[J]. 西安交通大学学报,2007,41(5): 507-511. XU Zili,GU Weiwei,LYU Qiang,et al. Study on damping structure parameters of blades based on the microslip model[J]. Journal of Xi’an Jiaotong University,2007,41(5): 507-511. (in ChineseXU Zili, GU Weiwei, LYU Qiang, et al. Study on damping structure parameters of blades based on the microslip model[J]. Journal of Xi’an Jiaotong University, 2007, 41(5): 507-511. (in Chinese) [16] 谷伟伟,徐自力,胡哺松,等. 微滑移阻尼叶片最优正压力的影响因素分析[J]. 西安交通大学学报,2008,42(7): 828-832. GU Weiwei,XU Zili,HU Busong,et al. Influence of structural parameters on optimal normal load of microslip damped blades[J]. Journal of Xi’an Jiaotong University,2008,42(7): 828-832. (in ChineseGU Weiwei, XU Zili, HU Busong, et al. Influence of structural parameters on optimal normal load of microslip damped blades[J]. Journal of Xi’an Jiaotong University, 2008, 42(7): 828-832. (in Chinese) [17] LAXALDE D,THOUVEREZ F,LOMBARD J P. Forced response analysis of integrally bladed disks with friction ring dampers[J]. Journal of Vibration and Acoustics,2010,132(1): 011013. doi: 10.1115/1.4000763 [18] ZUCCA S,DI MAIO D,EWINS D J. Measuring the performance of underplatform dampers for turbine blades by rotating laser Doppler vibrometer[J]. Mechanical Systems and Signal Processing,2012,32: 269-281. doi: 10.1016/j.ymssp.2012.05.011 -
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