numero26

S. Foletti et alii, Frattura ed Integrità Strutturale, 26 (2013) 123-131; DOI: 10.3221/IGF-ESIS.26.12 125 The theory behind the correlation of high temperature crack growth data essentially follows that of elastic-plastic fracture mechanics. The parameter to describe the creep crack growth behaviour has been discussed for a number of years [7, 8] and it is well known that for situations where linear elastic conditions prevail (short times and/or low loads) the linear elastic stress intensity factor, K, may be used to predict creep crack growth. For creep-ductile materials under steady state creep conditions however, the linear elasticity may no longer be applicable and the stress intensity factor do not properly characterize crack growth rates. This is demonstrated by considering influences of the load level and temperature. The crack tip stress and strain rate fields of ductile materials under steady crack growth are characterised by the parameter C* which can successfully correlate creep crack growth. The C* parameter is defined as the stabilized value of the parameter C(t) for t  , i.e. when the effect of creep caused the complete redistribution of stresses behind the crack tip:           * ( ) ( ) i u C C t W t dy T ds x (3) where Γ is a contour around the crack tip,  ( ) W t the strain energy density rate, T i the components of the traction vector and  i u the components of the displacement rate vector. By analogy between steady state creep and plasticity, the integral (3) is independent from the path  when elastic strain rates are negligible throughout the body. The reason why various creep condition do not affect the dependence of creep crack growth on the C* parameter is that the C* parameter itself already includes the effects of load level and temperature. That is, load level and temperature affect not only the creep crack growth rate but also the value of C* parameter. Once a steady-state distribution of stress and creep damage has been developed ahead of a crack tip, it is usually found that creep crack growth rate can be described by an expression of the form [9]:    * da D C dt (4) where D and φ are material constants. Nikbin et al. [10] demonstrated that the power dependence of C* varies only over the range 0.7-1 and the crack growth rate can be predicted by: 0.85 * 3 * f da C dt    (5) Eq. 5 represents the NSW Model and is also included in the statement of the BS 7910 rule for the estimation of the creep crack propagation ratio in components operating at high temperature. In this model the extremes of plane stress and plane strain conditions are predicted taking into account the decrease of creep ductility under multiaxial stress conditions. The multiaxial ductility * f  ranges between the uniaxial failure strain f  , for plain stress conditions, and 1/30 of the uniaxial failure strain for plain strain conditions [2, 9]. To verify the validity of the NSW model for the examined material, the C* parameter may be determined by experimental test of CCG based upon the load line displacement rate,   c ,    * c P C F B b (6) where P is the applied load, b the remaining ligament ahead the crack tip, B the net thickness, and F a factor dependent on crack length, specimen geometry and creep stress index n ; while in order to use the Eq. (5) for components, C* must be determined from finite element analysis or, in line with the used defect assessment codes, from reference stress method. In this paper a 12%Cr steel for turbine disk has been examined. CCG test on compact tension (CT) specimens according to the recommendations of ASTM-E1457 have been carried out in order to obtain K Ii characterizing the creep crack initiation of the material (Eq. 2) and to validate the Eq. (4) for the correlation between creep crack growth and C* parameter. For a turbine disk made of this examined 12%Cr steel, the 2CD diagram has been applied to study the occurrence of crack initiation on the component at the extreme stress level and temperature experienced in service and the correlation expressed by Eq. (5) has been used to compare the cracking behaviour of the turbine disk when C* is numerically calculated by FEM analysis and when it is calculated by reference stress solution. The usual load case for the turbine disk is a start/stop thermo-mechanical load including a hold time at high temperature, where this hold time load is high enough to cause time dependent effects such as creep deformation.