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对Ti-6Al-4V钛合金紧固孔试样进行了疲劳裂纹扩展试验。通过在随机载荷谱中添加标识谱,使断口上形成可判读的疲劳条带,采用疲劳条带与体视显微镜相结合的方法获得试样的随机载荷谱作用下孔边自然萌生裂纹扩展的a-N数据,并用SEM对疲劳断口观察。由TTCI反推EIFS方法,建立了描述孔边裂纹细节原始疲劳质量(IFQ)的当量初始缺陷尺寸(EIFS)分布,并进行了紧固孔符合性检查,满足控制要求。
Fatigue crack growth test was carried out on the Ti-6Al-4V titanium alloy fastening hole sample. By adding the identification spectrum to the random load spectrum, the fatiguable fatigue band can be formed on the fracture surface, and the combination of fatigue band and stereo microscope can be used to obtain aN Data, and SEM observation of fatigue fracture. Based on the TTCI inverse EIFS method, an equivalent initial defect size (EIFS) distribution describing the initial fatigue quality (IFQ) of the crack detail in the hole edge was established and the compliance hole inspection was performed to meet the control requirements.