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民用航空发动机TA19电子束焊疲劳试验

宋利 杨俊杰 陈铁峰

宋利, 杨俊杰, 陈铁峰. 民用航空发动机TA19电子束焊疲劳试验[J]. 航空动力学报, 2015, 30(1): 121-128. doi: 10.13224/j.cnki.jasp.2015.01.017
引用本文: 宋利, 杨俊杰, 陈铁峰. 民用航空发动机TA19电子束焊疲劳试验[J]. 航空动力学报, 2015, 30(1): 121-128. doi: 10.13224/j.cnki.jasp.2015.01.017
SONG Li, YANG Jun-jie, CHEN Tie-feng. Fatigue test of electron beam welding for TA19 in civil aircraft engine[J]. Journal of Aerospace Power, 2015, 30(1): 121-128. doi: 10.13224/j.cnki.jasp.2015.01.017
Citation: SONG Li, YANG Jun-jie, CHEN Tie-feng. Fatigue test of electron beam welding for TA19 in civil aircraft engine[J]. Journal of Aerospace Power, 2015, 30(1): 121-128. doi: 10.13224/j.cnki.jasp.2015.01.017

民用航空发动机TA19电子束焊疲劳试验

doi: 10.13224/j.cnki.jasp.2015.01.017
详细信息
    作者简介:

    宋利(1985-),男,四川泸州人,工程师,硕士,主要从事民用航空发动机高压压气机结构设计.

  • 中图分类号: V250.3

Fatigue test of electron beam welding for TA19 in civil aircraft engine

  • 摘要: 针对民用航空发动机钛合金整体叶盘常用材料TA19开展其母材试件与电子束焊焊接试件在20,300,450℃的疲劳试验,通过焊接试件的焊缝材料断口与母材断口形貌的比较探讨了焊缝材料的疲劳破坏机理,并在104~106循环的疲劳寿命区间内采用Basquin模型分别建立了焊缝材料和母材的应力-疲劳寿命(S-N)曲线,结果显示母材试件与焊接试件的试验疲劳寿命大部分都落在了对应模型计算疲劳寿命的2倍线之内,表明试验得到的S-N曲线是合理的.焊接试件与母材试件的S-N曲线的对比分析表明,20℃时焊接试件的疲劳性能比母材试件略高,而在300℃和450℃时焊接试件与母材试件的疲劳性能差异随应力水平发生变化.但总地说来,在所关注疲劳寿命区间内,母材试件与焊接试件的计算疲劳寿命差异也在2倍线以内,初步表明两者的疲劳性能相当.

     

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出版历程
  • 收稿日期:  2013-05-30
  • 刊出日期:  2015-01-28

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