applied fracture mechanics

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Fracture Analysis of Generator Fan Blades 325A simplified 3D model of airfoils was created using a geometry pre-processor programcalled OSM (Object Solid Modeler). A boundary element model of the geometry, consistingof triangular and square elements was then meshed within the FRANC3D program, and thestresses were applied by the model boundary conditions.To start the crack growth simulation in FRANC3D an initial crack was introduced into themodel. The initial crack was assumed to be a semi-elliptical surface crack witha0.1c ,based on previous fractographic findings. Initial crack length was computed from thethreshold stress intensity factor range based on the equation (Hertzberg, 1989):K Y a(7)th 0Taking Kthfrom the literature and values for the first and the second fractured bladesbased on the computed failure stresses and the positive portion of the stress cycle, and usingthe calculated values of Y from Newman–Raju equations (Newman & Raju, 1984), the initialcrack lengths below which crack growth is arrested, a0, were computed to beapproximatelyrespectively.48 10 5 m and 22 10 5m for the first and the second fractured bladesBased on the stresses applied by the model boundary conditions, the initial crack was grownin a series of crack propagation steps. Fig. 15a is a simplified 3D model of the airfoil that wasmeshed 2D (Boundary elements) in FRANC3D for simulating fatigue crack growth infractured blades. Fig. 15b shows simulated fatigue crack in blade No. 8 after three steps ofpropagation.Stress intensity factors at each step were calculated within FRANC3D and the fatigue crackgrowth curves were calculated using the Paris power law relationship given by (Broek,1995):danC KdN (8)The empirical constants C and n were computed by fitting the near threshold crack growthdata for AA 2124 aluminum alloy (Department of Defense, 1998) as13 nC 9.5 10 m.(MPa m) and n 4.9 for da dN expressed in m.cycle -1 at a load ratioof R 0.1 assumed in this case. The results of crack growth simulations in the first and thesecond fractured blades, where initial cracks are grown in small steps to their finaldimensions are plotted in Fig. 16. These curves show the crack size as a function of thenumber of applied stress cycles. It can be seen that the number of cycles required topropagate initial cracks to their final dimensions for the first and the second fractured bladesare just about61.3 10 and58 10 cycles respectively.
326Applied Fracture MechanicsStress calculations showed that the total stress acting on the third fractured blade (blade No.11) is higher than for the two other fractured blades. Therefore, it can be assumed that thefatigue crack growth life of this blade is the shortest one and has the least portion on thetotal fatigue crack growth life of the failed fan. Thus, the simulation of blade No. 11 fatiguecrack growth life was not performed and was ignored.Figure 15. (a) A 3D model of the airfoil with 2D mesh for simulating fatigue crack growth in FRANC3Dsoftware and (b) simulated fatigue crack in blade No. 8 after three steps of propagation
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PrefaceKnowledge accumulated in the
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Section 1Computational Methods of F
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Chapter 4Fracture of Dental Materia
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Fracture Mechanics Based Models of
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