一种基于模态的叶片缘板阻尼器减振设计方法

推进技术 ›› 2018, Vol. 39 ›› Issue (6): 1361-1368.

一种基于模态的叶片缘板阻尼器减振设计方法

毛辛男^1,2,王延荣^1,2

北京航空航天大学能源与动力工程学院，北京 100083; 先进航空发动机协同创新中心，北京 100083,北京航空航天大学能源与动力工程学院，北京 100083; 先进航空发动机协同创新中心，北京 100083

发布日期:2021-08-15
基金资助:
国家自然科学基金(51475022)。

An Efficient Design Method of an Underplatform Damper for Suppression of Blade Vibration in a Given Eigen-Mode

School of Energy and Power Engineering，Beihang University，Beijing 100083，China;Collaborative Innovation Center for Advanced Aero-Engine，Beijing 100083，China and School of Energy and Power Engineering，Beihang University，Beijing 100083，China;Collaborative Innovation Center for Advanced Aero-Engine，Beijing 100083，China

Published:2021-08-15

摘要/Abstract

摘要： 为了有效解决航空发动机中叶片缘板阻尼器的减振设计问题，在无需开展复杂耗时的非线性响应分析的情况下，提出了一种基于模态的叶片缘板阻尼器减振设计方法。采用半圆形缘板阻尼器的结构形式，根据归一化等效理论，将带有缘板阻尼器的转子叶片简化为以集总参数表示的单自由度模型。引入局部微滑动模型及刚度比例因子，给出了不同干摩擦模型的非线性摩擦力求解方程。针对给定的转子叶片许用振动应力，计算缘板阻尼器的阻尼比特性曲线，通过对比能量法与谐波平衡法的计算结果，验证了所提出方法的可行性及准确性，并获得了阻尼比随相关设计参数的变化规律。对于文中示例，给定许用振动应力幅值为[50MPa]，最佳缘板阻尼器质量约为7.34g，其峰值阻尼比约为0.33%。

关键词: 转子叶片；缘板阻尼器；减振设计；阻尼比

Abstract: To solve the problem of vibration-reduction design for underplatform dampers in aircraft engine， based on the single degree of freedom model， an effective method of vibration-reduction analysis was proposed without the need for conducting complex time-consuming nonlinear response analysis. Using a type of semi-circular damper structure， in the light of the normalized equivalent theory， the rotor blade with underplatform dampers has been simplified to the single degree of freedom model represented by lumped parameters. Introducing the local micro-slip model and stiffness ratio factor， the nonlinear friction force equations were derived for different dry friction models. From the perspective of the vibration stress of the rotor blade， the characteristic curve of damping ratio for underplatform dampers has been calculated. The feasibility and accuracy of the proposed method were verified by comparing the results of energy method and harmonic balance method， and the variation rule of damping ratio with the relevant design parameters was obtained. As for the model in this paper， given that the amplitude of vibration stress is 50MPa， the optimal mass of underplatform damper is about 7.34g， and the peak damping ratio is about 0.33%， providing a reference for the parametric design of dampers.

Key words: Rotor blade；Underplatform damper；Vibration-reduction design；Damping ratio

毛辛男,王延荣. 一种基于模态的叶片缘板阻尼器减振设计方法[J]. 推进技术, 2018, 39(6): 1361-1368.

MAO Xin-nan^1,2,WANG Yan-rong^1,2. An Efficient Design Method of an Underplatform Damper for Suppression of Blade Vibration in a Given Eigen-Mode[J]. Journal of Propulsion Technology, 2018, 39(6): 1361-1368.

参考文献

[1] 王延荣, 田爱梅. 叶/盘结构振动分析中几个问题的探讨[J]. 推进技术, 2002, 23(3): 233-236. (WANG Yan-rong, TIAN Ai-mei. Discussion on Several Problems in Vibration Analysis of Bladed-Disk Assemblies [J]. Journal of Propulsion Technology, 2002, 23(3): 233-236.)
[2] 陈璐璐, 张大义, 文敏, 等. 带凸肩风扇叶片振动特性及设计方法研究[J]. 推进技术, 2015, 36(9): 1389-1394. (CHEN Lu-lu, ZHANG Da-yi, WEN Min, et al. Dynamical Effects of Shrouds on Fan Blade Vibration and Its Corresponding Design Method[J]. Journal of Propulsion Technology, 2015, 36(9): 1389-1394.)
[3] Griffin J H. Friction Damping of Resonant Stresses in Gas Turbine Engineering Airfoils[J]. Journal of Engineering for Power, 1980, 102(2): 329-333.
[4] Cigeroglu E, An N, Menq C H. A Microslip Friction Model with Normal Load Variation Induced by Normal Motion[J]. Nonlinear Dynamics, 2007, 50(3): 609-626.
[5] Panning L, Sextro W, Popp K. Optimization of Interblade Friction Damper Design [C]. Munich: ASME Turbo Expo 2000: Power for Land, Sea, and Air, 2000.
[6] Petrov E P, Ewins D J. Advanced Modeling of Underplatform Friction Dampers for Analysis of Bladed Disk Vibration[J]. Journal of Turbomachinery, 2006, 129(1): 143-150.
[7] CHEN Yu-di, WANG Yan-rong. A Method for the Resonant Response Evaluation of Blades System with Underplatform Dampers[C]. Guiyang: 6th International Symposium on Instrumentation & Control Technology Sensors Automatic Measurement Control & Computer Simulation, 2014.
[8] 郝燕平, 单颖春, 朱梓根. 缘板摩擦阻尼器的减振实验研究[J]. 航空动力学报, 2001, 16(1): 55-58.
[9] Zmitrowicz A. A Vibration Analysis of a Turbine Blade System Damped by Dry Friction Forces[J]. International Journal of Mechanical Sciences, 1981, 23(12): 741-761.
[10] Berthillier M, Dupont C, Mondal R, et al. Blades Forced Response Analysis with Friction Dampers[J]. Journal of Vibration & Acoustics, 1998, 120(2): 468-474.
[11] Zucca S, Firrone C M. Nonlinear Dynamics of Mechanical Systems with Friction Contacts: Coupled Static and Dynamic Multi-Harmonic Balance Method and Multiple Solutions[J]. Journal of Sound & Vibration, 2014, 333(3): 916-926.
[12] MA Hui, YIN Fan-lin, WU Zhi-yuan, et al. Nonlinear Vibration Response Analysis of a Rotor-Blade System with Blade-Tip Rubbing[J]. Nonlinear Dynamics, 2016, 84(3): 1225-1258.
[13] 单颖春. 叶轮机械叶片干摩擦减振研究[D]. 北京:北京航空航天大学, 2002.
[14] 倪振华. 振动力学[M]. 西安:西安交通大学出版社, 1989.
[15] Koh K H, Griffin J H, Filippi S, et al. Characterization of Turbine Blade Friction Dampers [J]. Journal of Engineering for Gas Turbines & Power, 2005, 127(4): 237-245.
[16] Rao S S(著). 李欣业, 张明路 (译). 机械振动[M]. 北京:清华大学出版社, 2009.
[17] Sanliturk K Y, Ewins D J, Stanbridge A B. Underplatform Dampers for Turbine Blades: Theoretical Modeling, Analysis, and Comparison with Experimental Data[C]. Indiana: ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, 1999.
[18] Allara M. A Model for the Characterization of Friction Contacts in Turbine Blades[J]. Journal of Sound & Vibration, 2009, 320(320): 527-544.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2017-05-24；修订日期:2017-06-21。基金项目:国家自然科学基金(51475022)。通讯作者:毛辛男,男,硕士生,研究领域为航空发动机转子叶片振动抑制。E-mail: maoxn0720@buaa.edu.cn