With the growing size of wind turbine rotor blades, it is unrealistic to expect composite laminates used in a
rotor blade structure to be free from defects. Instead, it would be appropriate to accept that damages will form
in these laminates either from manufacturing defects and then try to limit or allow damage growth in a stable
manner or arrest. Fortunately, most fibre composite materials are damage tolerant and can exhibit increased
fracture resistance under stable damage growth.
Delamination is one of the critical damage types seen in composite structures which is often associated with
loss in stiffness and overall load-carrying capability and can eventually lead to structural failure [1]. The
delamination crack growth may be characterized by the material fracture resistance, known as R-curve [2],
which is a graph showing the J-integral as a function of the crack growth, as shown in Figure 1. The fracture
resistance is the value of the J-integral when the crack grows, defined by J0 for crack-tip initiation and Jss for
steady-state crack growth. The R-curve as such has been shown not to be a material property but depend on
specimen size [2]. Instead, it has been shown that the J integral as a function of end-opening and cohesive
laws (traction as a function of separation are independent of specimen size). The present work aims to
determine cohesive laws from R-curves in two different composite materials undergoing delamination. In the present study, an experimental campaign was carried out to extract cohesive laws for two different
unidirectional composites: i) Material A and ii) Material B. Both these materials have common UD fabric
but different resins: vinylester and flexible resin (with very high elongation) respectively. Test laminates
with pre-inserted slip foil were made by vacuum infusion. Specimens of dimensions 500 mm x 24 mm were cut form each laminate plate and bonded with high strength steel beams of thickness 2 mm on both sides.
Prior to bonding of steel beams, surface of the laminate was grinded slightly (removing about 0.5 mm) so
that the surface was plane, and fibres were exposed making stronger adhesion with the steel beams. Static
Double Cantilever Beam (DCB) testsloaded by pure bending moments were performed on the two specimen
series under displacement control. Digital Image Correlation was used to measure crack end opening
displacements. Further, two acoustic emission sensors were mounted on DCB specimens to record
delamination damage growth activities. Two cameras were used to record the DCB test, one camera
positioned near to crack tip for extracting end openings and the other having large field of view to capture
specimen curvature
DUGiDocs