Issue34

T. Itoh et alii, Frattura ed Integrità Strutturale, 34 (2015) 487-497; DOI: 10.3221/IGF-ESIS.34.54 495 scratches yielded in machining. In the λ=0.4 test with the non-polishing specimen, a straight crack is observed propagating along the cutting scratch. Fig. 13 shows Mohr’s stress circles and principal shear stress planes with normal and shear stresses on their planes in each λ state. At λ=0, the equivalent maximum shear stresses planes exists on planes normal and 45 degree incline to free surfaces. These two planes intersect with the surface plane in directions of 45 degree and normal to the specimen axis, respectively. So there are two possibilities of crack propagation which may results in the different crack mode between polish and non-polish specimens. In the λ=0.4 test, the maximum shear stress plane is 45 degree incline to the free surface on which normal and shear stresses are 493 MPa. The second principal shear stress plane is normal to the free surface of which normal and shear stresses are 693MPa and 293MPa, respectively. On this plane, the shear stress is much smaller but the normal stress is larger than those on the maximum shear stress plane. Comparing the equivalent Mises’ stresses on these planes, the values have a small difference, 985MPa on the maximum shear stress plane and 858MPa on the second principal shear stress plane, which may suggests that which plane cracks propagate is undecidable depending on specimen surface condition. The crack mode may be affected by the specimen surface condition in uniaxial and biaxial fatigue tests and the difference in the crack mode has a possibility affecting on failure lives largely in the biaxial fatigue tests. However, more detail crack observation and discussion will be required about the crack modes in biaxial stress condition. λ λ=0 λ=0.4 λ=0.5 λ=1.0 Polish Non polish Axial direction 400 μm Figure 12 : Main crack shape on the surface of specimen.  λ=0 λ=0.4 λ=0.5 λ=1.0 Mohr’s stress circle Shear stress planes σ 2 σ 3 τ σ σ 1 σ 3 τ σ σ 1 σ 2 σ 3 σ 1 τ σ σ 2 σ 3 σ 1 τ σ σ 2 400 400 400 400 693 293 462 462 693 231 493 493 400 400 400 400 Figure 13 : Mohr’s stress circle and maximum shear plane in principal stress ratio.