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钛合金大孔径开缝衬套冷挤压工艺研究
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摘要
开缝衬套冷挤压强化技术是提高飞行器结构件连接孔疲劳寿命最有效的方式之一,本文以孔径为大孔径的钛合金为研究对象,分别对不同夹层厚度及不同理论干涉量情况下的披拉力、实际干涉量以及强化后疲劳试验板疲劳增益进行分析。试验结果表明:在试验参数范围内,拔拉力的大小不仅受干涉量的影响,而且受夹层厚度的影响。发现开缝衬套冷挤压强化的理论干涉量与实际干涉量之间存在一定的函数关系。即y=-6.9167×2+1.3578×-0.0191。在冷挤压强化后试验件寿命明显提高,与未强化的试验件相比,理论干涉量为3%和4%的冷挤压强化试验件疲劳寿命提高约3~20倍,故实际工程应用时,理论干涉量建议不小于3%。
Split sleeve cold extrusion strengthening technology is to improve the aircraft of the connecting hole fatigue life is the most effective way,in this paper,the- titanium alloy with an aperture of large hole is as the research object,the drawing force、the actual interference amount and the fatigue gain of the strengthened after the different thickness and different of the layer are analyzed。 The experimental results show that,in the range of experimental parameters,the drawing force is affected not only by the amount of interference,but also by the thickness of the layer。 There is a certain relation between Split sleeve cold extrusion strengthening theory of interference amount and the actual amount of interference,namely y =-6.9167x2 + 1.3578x-0.0191 。The fatigue life of test specimen is obviously increased after cold expansion,Compared with the unstrengthened test specimens,the theoretical interference is 3%~4%,and the fatigue life is increased by about 3~20 times。 Therefore,in practical engineering applications the theoretical interference amount is not less than 3%.
引文
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