1. A method comprising: receiving, at a processing system, at least one vibration response parameter associated with an airfoil, wherein the at least one vibration response parameter comprises at least one of an airfoil excitation frequency, an airfoil vibration amplitude, and an airfoil structural damping; using the processing system for: computing a modal stress intensity factor (SIF) of at least one cracked airfoil finite element model using fracture mechanics based finite element analysis; and computing a vibratory SIF based, at least in part, on the modal SIF and a scaling factor comprising a variable number based on the at least one vibration response parameter; and computing a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.
1. A method comprising: receiving, at a processing system, at least one vibration response parameter associated with an airfoil, wherein the at least one vibration response parameter comprises at least one of an airfoil excitation frequency, an airfoil vibration amplitude, and an airfoil structural damping; using the processing system for: computing a modal stress intensity factor (SIF) of at least one cracked airfoil finite element model using fracture mechanics based finite element analysis; and computing a vibratory SIF based, at least in part, on the modal SIF and a scaling factor comprising a variable number based on the at least one vibration response parameter; and computing a residual life indicator of the airfoil based, at least in part, on the vibratory SIF. 2. The method of claim 1 , further comprising computing at least one mean SIF of the at least one cracked airfoil finite element model using fracture mechanics based finite element analysis; and wherein computing the residual life indicator further comprises taking into account the at least one mean SIF.