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航空发动机卡箍装配应力试验与装配参数控制方法

刘中华 贾铎 王鑫

刘中华, 贾铎, 王鑫. 航空发动机卡箍装配应力试验与装配参数控制方法[J]. 航空动力学报, 2020, 35(2): 368-377. doi: 10.13224/j.cnki.jasp.2020.02.016
引用本文: 刘中华, 贾铎, 王鑫. 航空发动机卡箍装配应力试验与装配参数控制方法[J]. 航空动力学报, 2020, 35(2): 368-377. doi: 10.13224/j.cnki.jasp.2020.02.016
LIU Zhonghua, JIA Duo, WANG Xin. Clamp assembly stress test of aero-engine and assembly parameter control method[J]. Journal of Aerospace Power, 2020, 35(2): 368-377. doi: 10.13224/j.cnki.jasp.2020.02.016
Citation: LIU Zhonghua, JIA Duo, WANG Xin. Clamp assembly stress test of aero-engine and assembly parameter control method[J]. Journal of Aerospace Power, 2020, 35(2): 368-377. doi: 10.13224/j.cnki.jasp.2020.02.016

航空发动机卡箍装配应力试验与装配参数控制方法

doi: 10.13224/j.cnki.jasp.2020.02.016

Clamp assembly stress test of aero-engine and assembly parameter control method

  • 摘要: 通过理论公式推导分析影响卡箍装配应力的主要参数,并通过试验方法对影响卡箍装配应力的因素进行了系统分析与研究,以3种规格、每种规格5个样本的卡箍作为试验对象,测试并统计分析螺栓拧紧力矩值、加载次数、装配方法对卡箍的应力影响规律。研究结果表明:靠近螺栓孔的卡箍表面为应力集中位置,卡箍随加载次数的增多应力呈降低趋势,但重复加载次数不宜过多,会导致卡箍局部较大的变形和磨损,增加2 mm垫片的方法对降低卡箍应力水平的效果最好,下降率可达468%;相比之下,限制卡箍位移后加载的方法应力下降率约为364%,而加载后校正的方法应力下降率约为286%。

     

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出版历程
  • 收稿日期:  2019-09-17
  • 刊出日期:  2020-02-28

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