Transverse behavior and acoustic-emission analysis of titanium metal-matrix composites under tensile loading

Wu, Xinhua; Mori, Hisashi; Bowen, P.

doi:10.1007/s11661-001-0160-4

Cited by 3 publications

(2 citation statements)

References 17 publications

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“…The fibre/matrix debond location was identified to be within the carbon layers at the fibre-matrix interface and the debond strength was found to be almost negligible. The low debond strength between the carbon layers in the interface is in agreement with several previous studies of continuously-reinforced MMCs containing SiC-based fibres [20,[24][25][26][27][28].…”

Section: Discussionsupporting

confidence: 92%

Evaluation of the Fibre-Matrix Debond Strength of a Ti-22Al-23Nb (AT.%)/Trimarc Metal Matrix Composite

LeBoeuf

Boehlert

2010

Advanced Composites Letters

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Silicon carbide fibre reinforced titanium metal matrix composites are of interest for engineering applications which require high strength, high temperature, low weight and damage tolerance [12-14]. Developing experimental methods to characterize and analyze their mechanical properties is of critical importance so that deformation and failure mechanisms can be established. It has been found that mechanical test specimen geometry is important for determining the fibre-matrix debond strength in continuous fibre reinforced metal matrix composites (MMCs) [2,4-8,10,11,15-19]. Specimens containing exposed fibres lead to edge stress singularities at the fibre/matrix interface for fibre orientations which are perpendicular to the applied stress. This stress singularity leads to fibre/matrix debonding at the specimen edge without the application of an externally applied mechanical load. Accurate determination of the debond strength is difficult using such a specimen geometry. A cruciform specimen geometry mitigates this edge effect by requiring the greatest stresses to be at the centre of the sample, thereby forcing the debond to occur at the centre of the cruciform [2,4-8]. Fig. 1 gives the dimensions of the experimental cruciform specimen designed to promote debond occurrences at the centre of the cruciform. The centre wing has been added to the traditional dogbone specimen so that the free edges of the wing are stress free. The largest stress occurs in the centre region of the specimen. The strain can be measured at this location using a strain gage placed Letter

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Section: Discussionsupporting

confidence: 92%

Evaluation of the Fibre-Matrix Debond Strength of a Ti-22Al-23Nb (AT.%)/Trimarc Metal Matrix Composite

LeBoeuf

Boehlert

2010

Advanced Composites Letters

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“…The primary transversely loaded SCS-6/Ti-6Al-2Sn-4Zr-2Mo (wt pct) composite containing 32 vol pct fibers [32] and, more recently, in Sigma-1140/Ti-6Al-4V (wt pct) single-fiber cruciform experiments [34] and Sigma-1140/Ti-6Al-4V (wt pct) composites containing 8 and 21 vol pct fibers. [34,35,36] Thus, the C layer appears to be a weak link in both the MMC and CMC interfaces. In the current material, failure in the carbon layer occurred in a number of locations, indicating similar strength throughout the carbon layer.…”

Section: Bond Strengthmentioning

confidence: 99%

Application of the cruciform specimen geometry to obtain transverse interface-property data in a high-fiber-volume-fraction SiC/Titanium alloy composite

Boehlert

Majumdar

Miracle

2001

Metall Mater Trans A

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A combined experimental and computational methodology was used to determine the relevant strength and residual-stress parameters in a manufactured, high-fiber-volume-fraction multiply metal matrix composite (MMC). The method was similar to that previously demonstrated on single-fiber composites, which had an extremely low fiber volume fraction. Variabilities in residual stresses and debond strengths in high-fiber-volume-fraction multiply composites, as well as current demands on the micromechanics-based computational prediction and validation of complex composite systems, necessitated the establishment of the test methodology described here. The model material chosen for this investigation was a plasma-processed six-ply, unidirectional Sigma-1240/Ti-6Al-2Sn-4Zr-2Mo (wt pct) MMC containing 32 vol pct continuous fibers. Room-temperature transverse tensile experiments were conducted on cruciform specimens. In addition, rectangular specimens were also evaluated in order to verify their applicability in obtaining valid interfacial property data. Debonding events, evaluated at different positions within a given specimen geometry, were captured by stress-strain curves and metallographic examination. Analytical and finite-element stress analyses were conducted to estimate the geometrical stress-concentration factors associated with the cruciform geometry. Residual stresses were estimated using etching and computational procedures. For the cruciform specimens, the experimental fiber-matrix debond strength was determined to be 22 MPa. Separation occurred within the carbon-rich interfacial layer, consistent with some previous observations on similar systems. Thus, the cruciform test methodology described here can be successfully used for transverse interfacialproperty evaluation of high-fiber-volume-fraction composites. For the rectangular specimens, the strain gages at different positions along the specimen width confirmed that the interface crack had initiated from the free edge and propagated inward. Hence, rectangular specimens cannot be used for valid interface strength measurements in multiply composites.

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The effect of molybdenum on the microstructure and creep behavior of Ti–24Al–17Nb–xMo alloys and Ti–24Al–17Nb–xMo SiC-fiber composites

Quast

Boehlert

2008

J Mater Sci

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Transverse behavior and acoustic-emission analysis of titanium metal-matrix composites under tensile loading

Cited by 3 publications

References 17 publications

Evaluation of the Fibre-Matrix Debond Strength of a Ti-22Al-23Nb (AT.%)/Trimarc Metal Matrix Composite

Evaluation of the Fibre-Matrix Debond Strength of a Ti-22Al-23Nb (AT.%)/Trimarc Metal Matrix Composite

Application of the cruciform specimen geometry to obtain transverse interface-property data in a high-fiber-volume-fraction SiC/Titanium alloy composite

The effect of molybdenum on the microstructure and creep behavior of Ti–24Al–17Nb–xMo alloys and Ti–24Al–17Nb–xMo SiC-fiber composites

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