Volume 32 Issue 5
May  2017
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Study on key factors of mistuned vibration for blade-disk system of some-stage compressor[J]. Journal of Aerospace Power, 2017, 32(5): 1082-1090. doi: 10.13224/j.cnki.jasp.2017.05.008
Citation: Study on key factors of mistuned vibration for blade-disk system of some-stage compressor[J]. Journal of Aerospace Power, 2017, 32(5): 1082-1090. doi: 10.13224/j.cnki.jasp.2017.05.008

Study on key factors of mistuned vibration for blade-disk system of some-stage compressor

doi: 10.13224/j.cnki.jasp.2017.05.008
  • Received Date: 2015-08-25
  • Publish Date: 2017-05-28
  • Based on the blade disk basic sector of certain stage compressor, blade disk finite element model considering non-linear tenon contact was established, free-interface substructure-fixed interface prestressed modal synthesis super element approximate analysis method was proposed, meanwhile, mistuned parameters recognition method of linear expression was fitted based on the blade static-frequency test and dichotomy combined with finite element analysis, exploring the effects of mistuning key factors on blade disk vibration. Results show that the non-linear tenon contact cannot be neglected, and the accuracy of super element method is 3.07%, so the proposed method meets the requirement. In addition, blades mean frequency, disk stiffness ratio and frequency veering have an effect on mistuned bladed disks vibration amplitude, resonance frequency and strain energy and other parameters.

     

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