Issue 47

J. P. Manaia et alii, Frattura ed Integrità Strutturale, 47 (2019) 82-103; DOI: 10.3221/IGF-ESIS.47.08 85 0 1 ln 1 3 2 h eq a R             (2) where R , is the notch radius, a 0 is the minimum and initial radius of the centre of the median cross-section and ln , is the naeperian logarithm. If  0 R the equation above is not valid, and if  R , the geometry of the specimen tends to that of a smooth cylindrical for which stress triaxiality ratio is   1 3 [4,12]. Bridgman formula was revisited by Bao and Wierzbicki using finite element simulation, being proposed a corrected equation with a coefficient of 2 [4]:          0 1 2 ln 1 3 2 a R (3) An initial minimum radius 0 a of 2.5 mm was chosen for the two geometries. The initial stress triaxiality ratio is equal to 0.39 and 0.64 for R=30 and R=5 specimens, respectively. As expected the stress triaxiality ratio increases inversely to the notch radius of specimens[4]. The shapes and dimensions of the flat notched specimens, for uniaxial positive loading path, are illustrated in Fig. 2. Two different notch radii: R=30 mm and R=5 mm, are assigned, similarly to the cylindrical geometry. Figure 2 : Flat notched specimens: (1) radius of 30 mm and (2) radius of 5 mm. (Dimensions in millimeters). The Bridgman stress triaxiality formula was derived for the point inside the notch of a flat notched plane strain specimen by Bai et al. [4]. Test results on 2024-T351 aluminium alloy and finite element simulations corroborated this formula. At the centre of the median cross-section the stress triaxiality ratio  is maximum and is given by the following equation [4]:                 3 1 2 ln 1 3 4 t R (4) where t is the ligament thickness of the flat notched specimen, R is the notch radius and ln is the naeperian logarithm [4]. An initial minimum ligament thickness t of 5 mm was chosen for the two geometries. Equation above implies that the range of stress triaxiality at the centre of a plane strain specimen is   1 3 . The initial stress triaxiality ratio is equal to 0.62 and 0.84 for R=30 mm and R=5 mm notch radii, respectively. Butterfly specimens under combined tensile/shear loading were investigated according three different loading angles,  = 0° (pure shear),  = 30° (both combined shear and tension) and  = 90° (pure tension) using specific designed butterfly specimen. The specimen dimensions and shape are shown in Fig. 3. Note that a similar specimen shape was designed by Bai [4], for 2024-T351 aluminium alloy and A710 steel. (1) (2)