Volume 35 Issue 11
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HU Dianyin, LI Wenzhu, LIU Hui. Numerical simulation on cold expansion strenghthening ,technology process of GH4169,[J]. Journal of Aerospace Power, 2020, 35(11): 2241-2247. doi: 10.13224/j.cnki.jasp.2020.11.001
Citation: HU Dianyin, LI Wenzhu, LIU Hui. Numerical simulation on cold expansion strenghthening ,technology process of GH4169,[J]. Journal of Aerospace Power, 2020, 35(11): 2241-2247. doi: 10.13224/j.cnki.jasp.2020.11.001
shu

Numerical simulation on cold expansion strenghthening ,technology process of GH4169,

doi: 10.13224/j.cnki.jasp.2020.11.001
  • 1.

    Research Institute of Aero-Engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • 2.

    Beijing Key Laboratory of Aero-Engine Structure and Strength,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • 3.

    School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • Received Date: 2020-04-08
  • Publish Date: 2020-11-28
    Abstract
  • On the basis of verifying the correctness of the three-dimensional finite element model for the cold expansion (CE) of central hole fatigue specimen of nickel-based superalloy GH4169, the influences of chamfering size, the order of chamfering-CE process and the reaming amount on circumferential residual stress distribution around the hole edge were studied through element deletion method. The results showed that the initial chamfer size less than the interference amount of the mandrel can reduce the residual compressive stress after CE. Lower residual compressive stress can be obtained at the hole edge by using the CE-chamfering process. The reaming process can lead to the increase of residual stress at the entrance of the hole edge and the minimum residual stress may be removed. Thus, reaming should be avoided as much as possible after cold expansion strengthening.

     

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