Abstract
Fatigue tests of notched unidirectional titanium aluminide composite, SCS-6/Ti-24Al-11Nb (at. pct), were performed to characterize the failure modes and mechanisms that control the life of this material. Using middle-hole specimens tested over a range of stress levels, fatigue damage was documented by optical photography, elastic compliance measurements, and electrical potential drop measurements. It was found that a few dominant cracks form near the notch root and propagate into the composite matrix. Chemical removal of the matrix material and metallographic sectioning of fatigue specimens examined prior to failure revealed that extensive fiber bridging of the matrix cracks dominated the fatigue life. A detailed description of the failure modes and mechanisms of damage initiating in the vicinity of a circular hole is presented, and the relative roles of crack initiation and crack growth are discussed.
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