Volume 34 Issue 5
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Numerical investigation of composite fan blade vibration characteristics due to blade-casing rub[J]. Journal of Aerospace Power, 2019, 34(5): 997-1009. doi: 10.13224/j.cnki.jasp.2019.05.005
Citation: Numerical investigation of composite fan blade vibration characteristics due to blade-casing rub[J]. Journal of Aerospace Power, 2019, 34(5): 997-1009. doi: 10.13224/j.cnki.jasp.2019.05.005
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Numerical investigation of composite fan blade vibration characteristics due to blade-casing rub

doi: 10.13224/j.cnki.jasp.2019.05.005
  • Received Date: 2018-08-09
  • Publish Date: 2019-05-28
    Abstract
  • A full three-dimensional composite fan blade rubbing vibration calculating model was established. A complete composite fan blade modeling method was used to establish composite fan blade and casing solid element models. The influence of the blades’ centrifugal stiffness was taken into consideration, Bezier surface was used to fit casing nodes. Rubbing phenomena of three blades with difference stacking sequences were studied under the assumption of a two-nodal diameter casing distortion. Results indicated that the stacking sequence pattern had a great impact on the blade rub-impact vibration characteristic at low rotational speeds. The rotating speeds of maximum amplitude and unstable vibration regions of blade with 90° layers were relatively low. The rubbing dynamic characteristics of the composite fan blade can be controlled by the stacking sequence, and when the rotating speed was close to the first-order mode resonance point of the blade caused by the third engine order, or close to the second-order mode resonance position of the blade caused by the sixth engine order, non-steady blade rubbing vibrations were generated. The method and results have certain guiding significance to the study of the rubbing dynamic characteristics of composite fan blades.

     

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