Volume 31 Issue 8
Aug.  2016
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XU Feng, MA Yan-hong, ZHANG Li, HONG Jie. Non-deformability evaluation of aero-engine's case[J]. Journal of Aerospace Power, 2016, 31(8): 1921-1928. doi: 10.13224/j.cnki.jasp.2016.08.017
Citation: XU Feng, MA Yan-hong, ZHANG Li, HONG Jie. Non-deformability evaluation of aero-engine's case[J]. Journal of Aerospace Power, 2016, 31(8): 1921-1928. doi: 10.13224/j.cnki.jasp.2016.08.017

Non-deformability evaluation of aero-engine's case

doi: 10.13224/j.cnki.jasp.2016.08.017
  • Received Date: 2014-10-30
  • Publish Date: 2016-08-28
  • Based on the structure and dynamic characteristics of aero-engine's case, an evaluation method for the whole engine case's non-deformability under safety design regulations was established. In order to evaluate the non-deformability from three aspects: structure characteristics, deformation characteristics under steady load, and deformation characteristics under impact load, three parameters including structure normalized equivalent stiffness, clearance matching coefficient, and impact amplification coefficient were raised respectively. Then a non-deformability assessment on typical high bypass ratio turbofan engine was conducted. The result shows that using the ratio of equivalent stiffness of each cross section to maximal equivalent stiffness as the structure normalized equivalent stiffness, using the ratio of minimal clearance to maximal clearance of each cross section under steady loads as the clearance matching coefficient, and using the ratio of peak force of impact load to bearing's or mount's reaction force as the impact enlargement coefficient, all the three parameters can reveal the dangerous position of the whole engine's case and the response characteristics under ultimate load. This result can provide a reference for structural design and optimization of other aero-engine's cases.

     

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