CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS
M., I., J., M., L., W. (2007). CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS. EKB Journal Management System, 12(ASAT Conference, 29-31 May 2007), 1-9. doi: 10.21608/asat.2007.23996
Ibrahim K. M.; Mueller J.; Wagner L.. "CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS". EKB Journal Management System, 12, ASAT Conference, 29-31 May 2007, 2007, 1-9. doi: 10.21608/asat.2007.23996
M., I., J., M., L., W. (2007). 'CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS', EKB Journal Management System, 12(ASAT Conference, 29-31 May 2007), pp. 1-9. doi: 10.21608/asat.2007.23996
M., I., J., M., L., W. CORRELATION BETWEEN MICROSTRUCTURE AND FATIGUE PROPERTY OF TI-6AL-4V ALLOY USED IN AEROSPACE APPLICATIONS. EKB Journal Management System, 2007; 12(ASAT Conference, 29-31 May 2007): 1-9. doi: 10.21608/asat.2007.23996

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, Page 1-9  XML PDF (1.29 MB)
Document Type: Original Article
DOI: 10.21608/asat.2007.23996
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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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