Fatigue Crack Growth in a Unidirectional SCS-6/Ti-15-3 Composite [chapter]

P Kantzos, J Telesman, L Ghosn
Composite Materials: Fatigue and Fracture (Third Volume)  
An investigation was conducted to characterize and model the fatigue crack growth (FCG) behavior of a SCS-6/Ti-15-3 metal matrix composite. Part of the study was conducted using a fatigue loading stage mounted inside a scanning electron microscope (SEM). This unique facility allowed high magnification viewing of the composite fatigue processes and measurement of the near crack tip displacements. The unidirectional composite was tested in the [O]e (i.e longitudinal) and [90]e (i.e. transverse)
more » ... (i.e. transverse) orientations. For comparison purposes unreinforced matrix material produced by the identical process as the reinforced material was also tested. The results of the study reveal that the fatigue crack growth behavior of the composite is a function of specimen geometry, fiber orientation and the interaction of local stress fields with the highly anisotropic composite. In the case of [O]e oriented single edge notch (SEN) specimens and [90]e oriented compact tension (CT) specimens, the crack growth was normal to the loading direction. However, for the [O] e CT specimens the crack grew mostly parallel to the loading and the fiber direction. The unusual fatigue behavior of the [0] e CT spec imens was attributed to the specimen geometry and the associated high tensile -. Abstract An investigation was conducted to characterize and model the fatigue crack growth (FCG) behavior of a SCS-6/Ti-15-3 metal matrix composite. Part of the study was conducted using a fatigue loading stage mounted inside a scanning electron microscope (SEM). This unique facility allowed high magnification viewing of the composite fatigue processes and measurement of the near crack tip displacements. The unidirectional composite was tested in the [O]e (i.e longitudinal) and [90]e (i.e. transverse) orientations. For comparison purposes unreinforced matrix material produced by the identical process as the reinforced material was also tested. The results of the study reveal that the fatigue crack growth behavior of the composite is a function of specimen geometry, fiber orientation and the interaction of local stress fields with the highly anisotropic composite. In the case of [O]e oriented single edge notch (SEN) specimens and [90]e oriented compact tension (CT) specimens, the crack growth was normal to the loading direction. However, for the [O] e CT specimens the crack grew mostly parallel to the loading and the fiber direction. The unusual fatigue behavior of the [0] e CT spec imens was attributed to the specimen geometry and the associated high tensile bending stresses perpendicular to the fiber direction. These stresses resulted in preferential cracking in the weak interface reg i on perpendicular to the fiber direction. The interface region, and in particular the carbon coating surrounding the fiber proved to be the composites weakest link. In the [0]8 SEN the crack growth was confined to the matrix leaving behind unbroken fibers which bridged the cracked surfaces. As the crack grew longer, more fibers bridged the crack resulting in a progressive decrease in the crack growth rates and eventual crack arrest. The actual near crack tip displacement measurements were used in a proposed formulation for a bridging-corrected effective crack driving force, ~Keff' This parameter was able to account for most of the experienced bridging and correlated the [ 0] 8 SEN fatigue crack growth data reasonably well. Key Words: Metal Matrix Composite, Fatigue Crack Growth, Crack Bridging, Fatigue Mechanisms. As the crack grew longer, more fibers bridged the crack resulting in a progressive decrease in the crack growth rates and eventual crack arrest. The actual near crack tip displacement measurements were used in a proposed formulation for a bridging-corrected effective crack driving force, ~Keff' This parameter was able to account for most of the experienced bridging and correlated the [ 0] 8 SEN fatigue crack growth data reasonably well.
doi:10.1520/stp17745s fatcat:yjbf463apbcoheqxqze5v4cj6m