Analysis on 30CrMnSiA Bolt Cracking
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摘要: 本文针对某型飞机上的断裂螺栓和开裂螺栓进行了宏微观形貌分析、微区成分分析、金相组织检查及硬度测试,并进行了同批次螺栓氢含量和夹杂物测定、螺栓窝现场检查,结合断口氧化腐蚀情况获得了没有阶段性扩展痕迹、剪切唇(月牙区)等客观证据,对断裂源区的沿晶特征给出了新的解释,判断该螺栓为三向应力作用下的过载开裂。Abstract: In this paper, morphology and microstructure analysis, micro-area composition analysis, metallographic structure examination, hardness test, determination of hydrogen content and inclusion of the same batch bolt as well as field inspection of bolt socket of the fractured bolts and cracked bolts for X Aircraft were carried out. Combined with the objective evidences, such as fracture oxidation corrosion, no periodic extend crack or shear lips (crescent area), a new explanation of the intergranular characteristics of the fracture source region is given, and finally it is concluded that the bolt is overload cracking under the action of the three-dimensional stress.
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Key words:
- bolt cracking /
- three-dimensional stress /
- intergranular crack
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表 1 螺栓硬度测试结果HRC
测试件 测试结果/HRC 平均值
HRC换算
σb/MPa技术要求
σb/MPa断裂件 40.5 40.5 40.4 40.5 1258 1 175±100 开裂件 40.7 41.1 41.3 41.0 1277 1 175±100 表 2 氢含量分析结果
螺栓号 测试结果H/% 1 0.0002 0.0002 0.0002 2 0.0007 0.0007 0.0010 3 0.0005 0.0003 0.0003 4 0.0003 0.0003 0.0003 5 0.0003 0.0003 0.0002 -
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