CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Article 74, Volume 12, ASAT Conference, 29-31 May 2007, May 2007, Pages 1-9 PDF (1.29 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/asat.2007.23996 | ||
| Authors | ||
| Ibrahim K. M.1; Mueller J.2; Wagner L.3 | ||
| 1Researcher, Manufacturing Technology Dept., CMRDI, Cairo, Egypt. | ||
| 2Graduate student, Materials science and Engineering Dept., TU-Clausthal, Germany. | ||
| 3Professor, Materials science and Engineering Dept., TU-Clausthal, Germany. | ||
| Abstract | ||
| Ti-6Al-4V is one of the most commonly used titanium alloys in the aviation industry due to its high strength-to-weight ratio, high operating temperature, and corrosion resistance. In this study, two batches of Ti-6.3Al-4.17V samples were subjected to different thermomechanical processes. The first batch was treated below the β-transus temperature (980 °C) to get duplex structure (α+β), while the second batch was treated above β-transus temperature (1050 °C) to get lamellar structure. Rotating bending fatigue test was carried out using electropolishing surface condition. It is observed that the treatment above β-transus showed higher fatigue limit than the samples treated below the β-transus. This is attributed to the fine structure (lamellar structure) obtained at 1050 °C than the duplex structure (α+β) obtained at 980 °C. In addition, the fatigue crack initiation sites existing in the structures were determined. | ||
| Keywords | ||
| Ti-6Al-4V; β-transus; fatigue property; Electropolishing; fatigue crack initiation site; thermomechnaical treatment | ||
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