In situ observation on fatigue crack growth in SCS-6/Ti-15-3 composite at elevated temperatures

A newly designed 100-mm-long X-ray trichrome optics for imaging has been proposed. Its working X-ray photon energy is 35 keV. Since this optics has two alternate mirrors, it can simultaneously supply three types of images: absorption, phase-interference and angle-resolved contrast for a sample space of 7 mm width. Examples of imaging by this novel X-ray interferometer in medicine, biology and material science are presented.

/pdf/an-x-ray-trichrome-imaging-trinity-absorption-phase-2bmj7xmdgz.pdf

An X-Ray Trichrome Imaging `Trinity': Absorption, Phase-Interference and Angle-Resolved Contrast

An experimental investigation has been made on the effect of interface wear behavior on the change of interface shear sliding stress during high temperature fatigue in a SiC (SCS-6) fiber-reinforced Ti-15-3 alloy composite. An unnotched composite was subjected to a tension–tension fatigue test in a vacuum of 2×10 −3 Pa at 823 K under maximum stress of 600, 780 and 960 MPa with a frequency of 2 Hz and R =0.1. The progress of interface debonding and sliding in the composite during fatigue was directly observed by scanning electron microscopy (SEM). The post-fatigued morphology of the fiber–matrix interface was observed and evaluated quantitatively using atomic force microscopy (AFM). Abrasive wear due to frictional sliding was observed near the end of a fractured fiber and the amplitude of asperity roughness at the weared interface was found to decrease with increasing of fatigue cycles. The wear behavior along the fiber shows strong dependence on the interface relative sliding length. The dominant mechanism for the reduction in the shear frictional sliding resistance along the fiber was asperity wear of outer most carbon coating layer of the fiber with the relative sliding length. The interface wear during cyclic loading results in change of load transfer potential at the interface and its leads to the increase of matrix crack initiation resistance near the fiber fracture.

Interface damage mechanism during high temperature fatigue test in SiC fiber-reinforced Ti alloy matrix composite

The debonding behaviour at the fibre/matrix interface in a unidirectional continuous carbon-coated SiC fibre reinforced Ti-17 composite was investigated. Single fibre push-out testing on thin slice...

Investigation of interface debonding behaviour in a unidirectional SiC fibre reinforced Ti-17 composite by a single fibre push-out technique:

The effect of abrasive wear at frictional sliding interface on shear frictional resistance in fiber-reinforced composite has been studied using W fiber-reinforced epoxy model composite. The interface shear frictional resistance decreases with the increase of fiber-matrix relative interface sliding during pushout test. Observation of the matrix surface after the test shows that abrasive wear occurs on the matrix surface caused by the rough fiber during fiber sliding, and this wear results in the decrease of the shear frictional resistance. The coefficient of friction is separated into the contribution of wear and adhesion using a simple analysis. The contribution of wear increases with the increase of fiber surface roughness, and the total coefficient of friction decreases significantly with the proceeding of interface sliding due to the reduction of the wear contribution part.

Effect of wear on interface frictional resistance in fiber-reinforced composite: model experimental

Unnotched SiC (SCS-6) fiber-reinforced Ti-15-3 alloy composite is subjected to a tension-tension fatigue test in a vacuum of 2×10−3 Pa at 293 and 823 K with a frequency of 2 Hz and R=0.1. Direct observation of the damage evolution process during the test is carried out by scanning electron microscopy (SEM). Test temperature dependent and independent fatigue damage behaviors are observed. The early stage fiber fractures observed at the polished surface are not influenced by the test temperature; however, matrix crack initiation and propagation behaviors differ greatly with temperature. The evolution of interface wear damage also differs with temperature, becoming more severe at 823 K, and the interface wear damage zone increases with the increase of the number of fatigue cycles. The macroscopic fatigue damage appears as a modulus reduction associated with interface sliding, matrix crack propagation, and plastic deformation of the matrix. The deformation zone of the composite tested at 823 K spreads more than that at 293 K. The fatigue life of the composite tested at 823 K is longer than that at 293 K. This behavior is related to the difference in spread of the damage zone in the matrix.

Observation of fatigue damage process in SiC fiber-reinforced Ti-15-3 composite at high temperature

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Observation of fatigue damage process in SiC fiber-reinforced Ti-15-3 composite at high temperature