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Volume 32 Issue 10
Oct.  2006
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Journal of Beijing University of Aeronautics and Astronautics  > 2006  >  32(10): 1174-1179.
Hong Jie, Shi Yajie, Liu Shuguo, et al. Experiment of damping characteristic of non-rotating shrouded blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(10): 1174-1179. (in Chinese)
Citation: Hong Jie, Shi Yajie, Liu Shuguo, et al. Experiment of damping characteristic of non-rotating shrouded blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(10): 1174-1179. (in Chinese)
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Experiment of damping characteristic of non-rotating shrouded blade

  • School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 01 Jun 2006
  • Publish Date: 31 Oct 2006
    Abstract
  • A measurement system was designed to accurately measure dynamic responses of non-rotating shrouded blade, in which initial normal load can be put on the friction interface by a load disc accurately. The design principle of this system, the loading scheme and the test errors were described. The dynamic response of the first bending mode of the shrouded blade with different shroud contact angles and shroud places were measured under various initial normal loads on the interface and different exciting force. The effects of the initial normal load, shroud contact angle and shroud place on the friction damping were analyzed from the test data. The results indicate that there is an optimal preload under which the shroud contact can provides maximal performance in dissipating vibratory energy for a given exciting force; and the relative displacement between the interfaces larger, the dissipating vibratory energy more. The design of shroud contact angle and place should obey this rule.

     

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  • [1] Griffin J H. Friction damping of resonant stresses in gas turbine engine airfoils [J]. Journal of Engineering for Power, 1980, 102:329-333 [2] Srinivasan A V. Flutter and resonant vibration characteristics of engine blades [J]. Journal of Engineering for Gas Turbine and Power, 1997, 119:742-775 [3] Sanliturk K Y, Ewins D J. Modelling two-dimensional friction contact and its application using harmonic balance method [J]. Journal of Sound and Vibration, 1996, 193(2):511-523 [4] Yang B D, Menq C H. Characterization of 3D contact kinematics and prediction of resonant response of structure having 3D friction constraint [J]. Journal of Sound and Vibration, 1998, 217(5):909-925 [5] Petrov E P, Ewins D J. Generic friction models for time-domain vibration analysis of bladed discs Proceeding of ASME Turbo Expo 2003 GT-2003-38475.Atlanta, Georgia, USA:ASME, 2003 [6] Yang B D, Chen J J,Menq C H. Prediction of resonant response of shrouded blades with three-dimensional shroud constraint [J]. Transactions of ASME Journal of Engineering for Gas Turbines and Power, 1999, 121:523-529 [7] 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 Hao Yanping, Shan Yingchun, Zhu Zigen. Effects of platform friction damper on resonant stresses in gas turbine blades[J]. Journal of Aerospace Power, 2001, 16(1):55-58(in Chinese) [8] Szwedowicz J, Kissel M, Ravindra B, et al. Estimation of contact stiffness and its role in the design of a friction damper Proceeding of ASME Turbo Expo 2001, 2001-GT-0290. New Orleans:ASME,2001 [9] 单颖春. 叶轮机械叶片干摩擦减振研究 . 北京:北京航空航天大学能源与动力工程学院, 2002 Shan Yingchun. Investigation on the vibration control of turbo-machine blade by dry friction damping . Beijing:School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, 2002(in Chinese) [10] Shi Yajie, Hong Jie, Shan Yingchun, et al. Forced response analysis of shrouded blades by an alternating frequency/time domain method Proceeding of ASME Turbo Expo 2006 GT2006-90595. Barcelona, Spain:ASME, 2006
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