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航空发动机转子叶片的声振疲劳特性试验

王琰 郭定文

王琰, 郭定文. 航空发动机转子叶片的声振疲劳特性试验[J]. 航空动力学报, 2016, 31(11): 2738-2743. doi: 10.13224/j.cnki.jasp.2016.11.023
引用本文: 王琰, 郭定文. 航空发动机转子叶片的声振疲劳特性试验[J]. 航空动力学报, 2016, 31(11): 2738-2743. doi: 10.13224/j.cnki.jasp.2016.11.023
WANG Yan, GUO Ding-wen. Experiment on acoustic vibration fatigue properties of the aero-engine rotor blade[J]. Journal of Aerospace Power, 2016, 31(11): 2738-2743. doi: 10.13224/j.cnki.jasp.2016.11.023
Citation: WANG Yan, GUO Ding-wen. Experiment on acoustic vibration fatigue properties of the aero-engine rotor blade[J]. Journal of Aerospace Power, 2016, 31(11): 2738-2743. doi: 10.13224/j.cnki.jasp.2016.11.023

航空发动机转子叶片的声振疲劳特性试验

doi: 10.13224/j.cnki.jasp.2016.11.023
详细信息
    作者简介:

    王琰(1986-),女,宁夏固原人,工程师,硕士,主要从事结构声疲劳研究.

  • 中图分类号: V232.2

Experiment on acoustic vibration fatigue properties of the aero-engine rotor blade

  • 摘要: 由于振动载荷、声载荷等会造成航空发动机转子叶片的高周疲劳失效,通过试验研究了发动机转子叶片的声振疲劳特性.首先研究了叶根边界条件对发动机转子叶片声响应特性的影响,对3组叶片施加不同的顶紧力,由低到高施加声载荷,试验得到不同叶根边界条件下叶片的声响应与声载荷的关系,并且得出叶根边界条件对转子叶片声响应大小有影响的结论.随后研究了叶片的声振疲劳特性,得出以下结论:声载荷作用下,叶片确实可以发生破坏.在两种不同的激励方式(随机振动激励与正弦振动激励)作用下叶片的频率下降略有不同,并且在动应力水平相同的条件下,发动机转子叶片在正弦振动激励下的寿命远大于其在随机振动激励下的寿命.

     

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出版历程
  • 收稿日期:  2015-12-16
  • 刊出日期:  2016-11-28

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