PSI - Issue 5

Marcin Wachowski et al. / Procedia Structural Integrity 5 (2017) 422–429 Author name / Procedia - Social and Behavioral Sciences 00 (2016) 000 – 000

424

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Fig 1. Connection area of AA2519/Ti6Al4V with the intermediate layer of AA1050 alloy

Chemical composition of the alloys are presented in Tables 1 and 2. The scope of the research included conducting tests on two batches of samples. The first of them is the resulting AA2519/AA1050/Ti6Al4V laminate, subjected only to straightening by additional rolling. The second batch is a layered material AA2519/AA1050/Ti6Al4V, subjected to additional heat treatment.

Table 1. Chemical composition of AA2519 alloy.

Chemical composition [wt%] Si Fe Cu Mg

Zn

Ti

V Zr

Sc

0.06

0.08

5.77

0.18

0.01

0.04

0.12

0.2

0.36

Table 2. Chemical composition of Ti6Al4V alloy. Chemical composition [wt%] O V Al Fe H C

N

<0.20

3.5 5.5 <0.30

<0.0015

<0.08

<0.05

A comparison of the fatigue properties of laminate before and after the heat treatment is proposed in this research. The laminate is composed of base materials of 3 mm thickness (each). An additional 0.8 mm transition AA1050 alloy layer was required for the explosive welding process. The laminate was obtained by explosion welding at Zakład Technologii Wysokoenergetycznych “EXPLOMET”. The tested composite after formation was annealed at 530 – 550 °C for 2 h, quenched in water at room temperature and then aged at 165 °C for 10 h to strengthen it. Before the start of fatigue tests the basic strength properties of the laminate were checked [17-19]. The tensile tests were carried out for flat samples according to PN-EN ISO 6892-1:2010. Investigations aim to comparing the high cycle fatigue behavior of AA2519/AA1050/TI6AL4V laminate before and after heat treatment, based on experimental results from fatigue tests. On the basis of standards (ASTM E466, PN-74/H-04327, PN-EN 3987:2010) shapes samples for testing fatigue life were developed. The high cycle fatigue tests were performed using two types of specimens: flat with a central hole (Fig. 2a) and smooth - without hole (Fig. 2b). Research samples were cut from the sheet of the laminate using method of water jet cutting and then both shape series of 20 specimens have been treated.

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