Issue 35

S. Barter et alii, Frattura ed Integrità Strutturale, 35 (2016) 132-141; DOI: 10.3221/IGF-ESIS.35.16 136 testing, the fatigue cracks were fractographically examined using a field emission gun scanning electron microscope. The crack growth increments, due to the various load sub-blocks, were measured to obtain short crack growth data for comparison with standard da/dN data for this alloy. Figure 3 : A fatigue crack produced by a simple spectrum (insert) showing the crack path (A) across one grain and (B) two grains. The  K s for each CA growth bands are marked. Note the morphology and path changes with changing R . O BSERVATIONS AND THE DISCUSSION OF CRACK GROWTH IN AA7050-T7451 n example that demonstrates variation in crack growth plane and morphology with load cycles of differing R is given in Fig. 3 for a simple spectrum consisting of four different R CA sub-blocks. In Fig. 3A, the crack path is observed to vary significantly as it progresses though the material. The  K applicable for each sub-block of crack growth is indicated on the figure. The fatigue crack growth for each CA sub-block of R appears to have a preferred path through this grain, not only changing in orientation or tilting in relation to the general crack growth plane, but also twisting or rotating about this plane [11]. Of particular note in this figure is the crack growth from the R =0 loading sub-block which appears to have local twisted segments, producing an appearance of deep pockets for its period of growth. In contrast, on the commencement of the R =0.7 loads, these pockets abruptly disappear, although remnants in the form of the well-known river patterns persist, on what is then relatively smooth growth. This suggests that in this case the grains orientation is more ideally positioned for R =0.7 crack growth. The net effect of these wavelength of 355nm with a Q-switched (QS) pulse duration of 2µSec, period of 100µSec and a repetition rate of 1KHz. This produced a 10  m full width half maximum beam at a typical energy of 164  J/pulse at the position of laser focus. 800 slots were produced by 4 pulses laid next to each other in a row to give slots that were approximately 0.05mm long. 6 Thick plate AA7050-T7451, that is commonly used to manufacture major aircraft structures, has a large pre-recrystallization grain size from restricted rolling during manufacture. Although the recrystallization grain size may be small (about 10  m), the lack of deformation from the rolling leaves these sub-grains with orientations similar to the pre-recrystallization grains from which they were formed. The fatigue cracking treats these sub-grains as being essentially of the same orientation and results in the large facets seen in in many of the coupons tested here, e.g., Fig. 2A. A