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. 2017 Jun 16;10(6):658.
doi: 10.3390/ma10060658.

Fatigue Lifetime of Ceramic Matrix Composites at Intermediate Temperature by Acoustic Emission

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Free PMC article

Fatigue Lifetime of Ceramic Matrix Composites at Intermediate Temperature by Acoustic Emission

Elie Racle et al. Materials (Basel). .
Free PMC article

Abstract

The fatigue behavior of a Ceramic Matrix Composite (CMC) at intermediate temperature under air is investigated. Because of the low density and the high tensile strength of CMC, they offer a good technical solution to design aeronautical structural components. The aim of the present study is to compare the behavior of this composite under static and cyclic loading. Comparison between incremental static and cyclic tests shows that cyclic loading with an amplitude higher than 30% of the ultimate tensile strength has significant effects on damage and material lifetimes. In order to evaluate the remaining lifetime, several damage indicators, mainly based on the investigation of the liberated energy, are introduced. These indicators highlight critical times or characteristic times, allowing an evaluation of the remaining lifetime. A link is established with the characteristic time around 25% of the total test duration and the beginning of the matrix cracking during cyclic fatigue.

Keywords: acoustic emission; ceramic matrix composite; fatigue lifetime.

Conflict of interest statement

The authors declare no conflict of interest.

Figures

Figure 1
Figure 1
Applied stress for (a) Static fatigue test and (b) Cyclic fatigue test for four stages.
Figure 2
Figure 2
Evolution with the number of cycles of the linear density of acoustic energy recorded during loading part and unloading part of the cycles on SiCf/[Si-B-C] composites for two different applied loads (a) σ = 0.30 UTS and (b) σ = 0.36 UTS.
Figure 3
Figure 3
(a) Experimental mechanical curve of composite under monotonic tension at room temperature; (b) Evolution of elastic modulus for three tests; (c) Evolution of linear densities of acoustic events along the specimen axis during tensile tests at room temperature.
Figure 4
Figure 4
Schematic diagram: (a) elastic modulus determination for the first loading (Ech) of the stage and at the end of the stage (Efa) and (b) cumulated number and energy of acoustic emission signals calculated at the end of the first loading (Nch and Uch) and at the end of the stage (Nfa and Ufa).
Figure 5
Figure 5
Evolution versus the applied load of (a) ratio E/E0; (b) maximal strain and (c) internal friction. The index “ch” means the first loading of each stage and the index “fa”, the end of the stage.
Figure 6
Figure 6
Strain and cumulated AE energy vs. time during a static fatigue test (stage 1: 0.18 UTS, stage 12: 0.84 UTS).
Figure 7
Figure 7
Maximal strain and cumulated AE energy vs. number of cycles during a cyclic fatigue test (stage 1: 0.18 UTS, stage 5: 0.42 UTS).
Figure 8
Figure 8
Coupling of mechanical energy and acoustic energy (Sentry function) for (a) an incremental cyclic fatigue test and (b) an incremental static fatigue test.
Figure 8
Figure 8
Coupling of mechanical energy and acoustic energy (Sentry function) for (a) an incremental cyclic fatigue test and (b) an incremental static fatigue test.
Figure 9
Figure 9
Evolution versus the applied load of (a) the ratio N/NRt, (b) the ratio UEA/UEART. The index “ch” means the first loading of each stage and the index ”fa”, the end of the stage.
Figure 9
Figure 9
Evolution versus the applied load of (a) the ratio N/NRt, (b) the ratio UEA/UEART. The index “ch” means the first loading of each stage and the index ”fa”, the end of the stage.
Figure 10
Figure 10
Evolution versus the number of cycles the ratio RLU for differents applied load (a) 0.24 UTS; (b) 0.30 UTS; (c) 0.36 UTS and (d) 0.42 UTS.
Figure 11
Figure 11
Loops in the plane stress/strain for a cyclic fatigue tests at constant amplitude.
Figure 12
Figure 12
Evolution of the coefficient RAE for cyclic fatigue tests at constant amplitude with the number of cycles.
Figure 13
Figure 13
Evolution with the number of cycles of the linear density of acoustic energy recorded during (a) loading part and (b) unloading part of the cycles on SiCf/[Si-B-C] composites for a cyclic fatigue test at constant amplitude 0.36 UTS.
Figure 14
Figure 14
(a) Evolution of the coefficient RLU during cyclic fatigue at constant amplitude and highlight of two characteristic times at 25% and 47% of the lifetime duration (LT lifetime) on SiCf/[Si-B-C] composites; (b) Evolution of the average energy.
Figure 15
Figure 15
Evolution of damage mechanisms during cyclic fatigue tests at constant amplitude 0.36 UTS. For this test, the characteristics times are at 25% and 61% of the lifetime.

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