Effect of frequency and environment on fatigue behavior of a CVI SiC/SiC ceramic matrix composite at 1200°C

Ruggles‐Wrenn, M. B.; Christensen, D.T.; Chamberlain, Adam L.; Lane, J.E.; Cook, T. S.

doi:10.1016/j.compscitech.2010.11.008

Cited by 104 publications

(51 citation statements)

References 21 publications

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“…When the data are normalized by the fiber volume fraction in the loading direction (Figure 12b), the composite creep rupture properties are nearly the same, indicating that they are dominated by the fiber creep rupture properties. Recently, more work has been performed on fatigue in air and steam environments in different SiC/SiC systems in order to assess the effect of these variable loading conditions (Ruggles-Wren et al, 2011). Therefore, to maximize stress capability at temperature, it is necessary to have the strongest, most creep-resistant, and Figure 12.…”

Section: Cmc Properties and Designmentioning

confidence: 99%

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

Morscher

2014

Encyclopedia of Aerospace Engineering

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Ceramic matrix composites have become viable materials for jet engine applications. In particular, SiC fiber‐reinforced SiC matrix composites are being developed for hot section components of jet engine in order to reduce weight and increase temperature capability its of hot section. SiC/SiC composites can be fabricated by a variety of methods, including melt infiltration (MI), chemical vapor infiltration (CVI), and polymer infiltration pyrolysis. Composite properties vary significantly, depending on the processing approach, constituent content, and fiber architecture. Ultimately, for SiC/SiC composite performance, long‐time load‐carrying capability in oxidizing environments requires composites that have high matrix‐cracking stresses. The melt‐infiltrated composite system is the most developed SiC/SiC composite, can produce the highest matrix‐cracking stresses, and is expected to be inserted into a commercial jet engine application in the next few years. The critical factors for design associated with matrix crack formation are discussed with respect to possible composite variations within the melt‐infiltrated composite system; however, some of the trends observed should be transferable to the other composite systems described as well. In addition, current challenges for use of these materials in aero applications are discussed.

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Section: Cmc Properties and Designmentioning

confidence: 99%

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

Morscher

2014

Encyclopedia of Aerospace Engineering

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“…The prediction of fatigue damage and fatigue life for composites has been the subject of many investigations during recent years [8][9][10][11][12]. According to Liu [13], the fatigue life models are divided into three classes: residual strength-based model, stiffness degradation-based model, damage tolerance model.…”

Section: Introductionmentioning

confidence: 99%

A residual strength model for the fatigue strengthening behavior of 2D needled CMCs

Fang

Gao

Zhang

et al. 2015

International Journal of Fatigue

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“…Numerous recent studies investigated mechanical behavior of high-performance SiC/SiC composites at elevated temperature [17][18][19][20][21][22][23][24][25][26][27]. Efforts to assess the life-limiting behaviors of SiC/SiC CMCs have been focused mainly on the fiber-dominated properties.…”

Section: Matec Web Of Conferencesmentioning

confidence: 99%

Creep behavior in interlaminar shear of a Hi-Nicalon^TM/ SiC-B₄C composite at 1200^∘C in air and in steam

Ruggles‐Wrenn

Pope

2015

MATEC Web of Conferences

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Abstract. Creep behavior in interlaminar shear of a non-oxide ceramic composite with a multilayered matrix was investigated at 1200 • C in laboratory air and in steam environment. The composite was produced via chemical vapor infiltration (CVI). The composite had an oxidation inhibited matrix, which consisted of alternating layers of silicon carbide and boron carbide and was reinforced with laminated Hi-Nicalon™ fibers woven in a five-harness-satin weave. Fiber preforms had pyrolytic carbon fiber coating with boron carbon overlay applied. The interlaminar shear properties were measured. The creep behavior was examined for interlaminar shear stresses in the 16-22 MPa range. Primary and secondary creep regimes were observed in all tests conducted in air and in steam. In air and in steam, creep run-out defined as 100 h at creep stress was achieved at 16 MPa. Similar creep strains were accumulated in air and in steam. Furthermore, creep strain rates and creep lifetimes were only moderately affected by the presence of steam. The retained properties of all specimens that achieved run-out were characterized. Composite microstructure, as well as damage and failure mechanisms were investigated. The tested specimens were also examined using electron probe microanalysis (EPMA) with wavelength dispersive spectroscopy (WDS). Analysis of the fracture surfaces revealed significant surface oxidation, but only trace amounts of boron and carbon. Cross sectional analysis showed increasing boron concentration in the specimen interior.

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Effect of frequency and environment on fatigue behavior of a CVI SiC/SiC ceramic matrix composite at 1200°C

Cited by 104 publications

References 21 publications

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

A residual strength model for the fatigue strengthening behavior of 2D needled CMCs

Creep behavior in interlaminar shear of a Hi-Nicalon^TM/ SiC-B₄C composite at 1200^∘C in air and in steam

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Effect of frequency and environment on fatigue behavior of a CVI SiC/SiC ceramic matrix composite at 1200°C

Cited by 104 publications

References 21 publications

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

Fiber‐Reinforced Ceramic Matrix Composites for Aero Engines

A residual strength model for the fatigue strengthening behavior of 2D needled CMCs

Creep behavior in interlaminar shear of a Hi-NicalonTM/ SiC-B4C composite at 1200∘C in air and in steam

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Creep behavior in interlaminar shear of a Hi-Nicalon^TM/ SiC-B₄C composite at 1200^∘C in air and in steam