Effect of Heat Treatment on the Damage Tolerance Properties of Ti-6Al-2Zr-2V-1.5Mo ELI Alloy Plate

Xiao Xiang Wang; Song Xiao Hui

doi:10.4028/www.scientific.net/MSF.690.282

Paper Titles

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Investigation of the Fatigue Behavior of AlMg4.5Mn (EN AW-5083) in the Temperature Range -60 °C < T < 20 °C
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HomeMaterials Science ForumMaterials Science Forum Vol. 690Effect of Heat Treatment on the Damage Tolerance...

Effect of Heat Treatment on the Damage Tolerance Properties of Ti-6Al-2Zr-2V-1.5Mo ELI Alloy Plate

Abstract:

Effect of heat treatment on the damage tolerance properties of a newly developed middle strength high damage tolerance Ti-6Al-2Zr-2V-1.5Mo ELI alloy plate has been investigated in this paper by testing fracture toughness and fatigue crack-extending rate of the plate under three heat treatment conditions and fractograph inspection of the samples. It has been found that with the increasing of the primary annealing temperature from 900°C to 950°C, the fracture toughness increased and the fatigue crack extending rate decreased significantly. Microstructural observation has found that the crack expanded through the α beaming and mainly are perpendicular to the α orientation in the lamellar structure which annealed in α+β phase zone. For the Widmanstaten structure, which can be obtained from annealing in single β phase zone, the continuous grain boundary α phase and α beaming boundary hinder the crack expanding significantly.

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Periodical:

Materials Science Forum (Volume 690)

Pages:

282-285

DOI:

https://doi.org/10.4028/www.scientific.net/MSF.690.282

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Online since:

June 2011

Authors:

Xiao Xiang Wang, Song Xiao Hui

Keywords:

Fatigue Crack Growth Rate, Fracture Toughness, Titanium Alloy

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References

[1] James C. Williams, Edgar A. Starke, Jr. Progress in structural materials for aerospace systems, Acta Materialia 51 (2003) 5775–5799.

Google Scholar

[2] Robert Dilger, Holger Hickethier, Michael D. Greenhalgh, Eurofighter a safe life aircraft in the age of damage tolerance, International Journal of Fatigue, 31 (2009) 1017–1023.

DOI: 10.1016/j.ijfatigue.2008.05.014

Google Scholar

[3] Chun-xiao Cao, Change of Material Selection Criterion and Development of High Damage-Tolerant Titanium Alloy, Acta Metallurgica Sinica, 38 (2002) 4-11.

Google Scholar

[4] Ji-kui Zhang, Xiao-quan Cheng, Zheng-neng Li, Total fatigue life prediction for Ti-alloys airframe structure based on durability and damage-tolerant design concept, Materials and Design 31 (2010) 4329–4335.

DOI: 10.1016/j.matdes.2010.03.052

Google Scholar

[5] Ben-run Hu, Xue-ren Wu, Chuan-fu Ding, Fatigue small crack behavior of Ti-6Al-4V alloy, Journal of Aeronautical Materials, 20 (2004) 30-34.

Google Scholar