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

Tanaka, Yoshihisa; Kagawa, Yutaka; Liu, Yu Fu; Masuda, Chitoshi

doi:10.1016/s0921-5093(00)01934-1

Cited by 10 publications

(7 citation statements)

References 18 publications

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“…Due to the mismatch of the coefficient of thermal expansion (CTE) between the C fiber and the SiC matrix, a thermal residual stress (TRS) formed upon cooling from the fabricating temperature. The thermal residual stresses in the fiber and the matrix can be described as follows: 8,9 where σ, E , α, m , and f are the thermal residual stress, Young's modulus, the thermal expansion coefficients, the matrix, and the fiber, respectively. Δ T is the temperature difference between the fabrication temperature and the room temperature.…”

Section: Resultsmentioning

confidence: 99%

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Preparation of C/SiC Composites by Hot Pressing, Using Different C Fiber Content as Reinforcement

Ding

Dong

Zhou

et al. 2006

Journal of the American Ceramic Society

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Unidirectional C/SiC composites were successfully prepared by hot pressing at 1850°C under 20 MPa, using different fiber volume fractions (from 28 vol% to 55 vol%) as reinforcement. The densification process of the composites became increasingly difficult with increasing fiber volume fraction, and some small pores were still distributed in the intrabundle regions of the composites. The cracks, resulting from the residual thermal stress in the composites due to the mismatch of the thermal expansion coefficient of the matrix and the fiber, were distributed in the matrix. With the increase of fiber content, the mechanical properties of the composites could be improved and the composites exhibited an obvious noncatastrophic fracture behavior due to a decrease in the thermal residual stress and an increase in the fiber pull outs.

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Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Preparation of C/SiC Composites by Hot Pressing, Using Different C Fiber Content as Reinforcement

Ding

Dong

Zhou

et al. 2006

Journal of the American Ceramic Society

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“…Due to the surface modification, the failure occurs not at the interface but in a region very close to the interface. The effect of temperature on debonding is especially significant in metal matrix composite materials [20][21][22][23][24][25][26][27][28][29][30][31][32][33][34]. At elevated temperatures, thermomechanical fatigue accounts for the failure of these materials.…”

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confidence: 99%

“…Fatigue tests on reinforced titanium composites revealed various interface damage mechanisms [20][21][22][23][24][25][26][27]. Shear frictional sliding [20], interfacial debonding [21], fiber bridging [22], surface embrittlement [23], matrix ligament premature ductile shear [24], and crack deflection [25] are typical damage mechanisms observed.…”

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confidence: 99%

“…Shear frictional sliding [20], interfacial debonding [21], fiber bridging [22], surface embrittlement [23], matrix ligament premature ductile shear [24], and crack deflection [25] are typical damage mechanisms observed. These damage mechanisms could occur simultaneously depending on loading modes, but debonding always exists and is considered as the major mechanism.…”

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Energy Dissipation Criteria for Surface Contact Damage Evaluation

Gan¹

2012

Continuum Mechanics - Progress in Fundamentals and Engineering Applications

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IntroductionThis chapter presents the energy dissipation approach for analyzing surface contact damages in various materials, including composite materials. As known, surface contact is a very common phenomenon, which can be found in daily life and many scientific and engineering problems. The contact of different bodies can be modeled as indentation. Analysis of indentation and modeling of the deformation states of indented materials are often difficult because of the complexity of stress distributions within indentation zones. It is a l s o v e r y d i f f i c u l t t o e v a l u a t e s t r e s s s t a t e s i n r e g i o n s u n d e r n e a t h a n i n d e n t e d z o n e . Instrumental indentation has been performed on various materials including composite materials. Experimental studies on indention of coatings and brittle materials have been reported extensively, but the criterion for evaluating the extent of damage is not unified. Ductile materials deform relatively stable in indentation processes. While brittle materials are sensitive to compressive contact loadings in view of the formation of surface cracks. Therefore, it is difficult to find a unified stress or strain based damage criterion to characterize the damage evolution. Energy dissipation analysis may be more accurate to describe the deformation behavior of such materials. Specifically, under wedge indentation, the analysis should be investigated because the stress field has the singularity which limits the applicability of the strength criterion. In this chapter, the load-displacement relations with elastic-plastic responses of the materials associated with the indentation processes will be obtained to calculate the hysteresis energy. Lattice rotation measurement using electron backscatter diffraction (EBSD) technique will be performed in the region ahead of the indenter tip to measure the dimension of the contact damage zone (CDZ) and the results will be used to define the length scales in contact deformation. A unified criterion using the hysteresis energy normalized by the length scales will be established.Damage evolution in composite materials is very sensitive to the interaction of reinforcements and matrices in interface regions. For example, the development of damage in glass particle and fiber reinforced epoxy composite materials is strongly influenced by the interface debonding conditions [1]. However, the exact effect of bonding conditions on the performance of particle filled composite materials is still not fully understood. Kawaguchi and Pearson [2] reported that strong matrix-particle adhesion may lower the fatigue crack propagation resistance. While the studies on Si 3 N 4 nanoparticle filled epoxy composites www.intechopen.com Continuum Mechanics -Progress in Fundamentals and Engineering Applications

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Fabricating hollow turbine blades using short carbon fiber-reinforced SiC composite

Zhang

Cao

et al. 2013

Int J Adv Manuf Technol

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

Cited by 10 publications

References 18 publications

Preparation of C/SiC Composites by Hot Pressing, Using Different C Fiber Content as Reinforcement

Preparation of C/SiC Composites by Hot Pressing, Using Different C Fiber Content as Reinforcement

Energy Dissipation Criteria for Surface Contact Damage Evaluation

Fabricating hollow turbine blades using short carbon fiber-reinforced SiC composite

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