Gas Turbines: Ceramics

Tension-Compression Fatigue of a SiC/SiC Ceramic Matrix Composite at Elevated Temperature

[+] Author and Article Information
M. B. Ruggles-Wrenn, T. P. Jones

Department of Aeronautics and Astronautics,  Air Force Institute of Technology, Wright-Patterson Air Force Base, OH 45433-7765

J. Eng. Gas Turbines Power 134(9), 091301 (Jul 23, 2012) (6 pages) doi:10.1115/1.4006989 History: Received June 18, 2012; Revised June 18, 2012; Published July 23, 2012; Online July 23, 2012

Tension-compression fatigue behavior of a nonoxide ceramic composite with a multilayered matrix was investigated at 1200 °C in laboratory air. 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 an eight-harness-satin weave (8HSW). Fiber preforms had pyrolytic carbon fiber coating with boron carbon overlay applied. Tension-compression fatigue behavior was studied for fatigue stresses ranging from 80 to 200 MPa at a frequency of 1.0 Hz. The R ratio (minimum stress to maximum stress) was −1.0. Fatigue run-out was defined as 2 × 105 cycles. Fatigue limit was 80 MPa. Specimens that achieved fatigue run-out were subjected to tensile tests to failure to characterize the retained tensile properties. The material retained 100% of its tensile strength. Reductions in tensile modulus and in compressive modulus were negligible. Composite microstructure, as well as damage and failure mechanisms were investigated.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

(a) Typical microstructure. (b) Oxidation inhibited matrix consisting of alternating layers of SiC and B4 C. (c) Fibers and PyC fiber coating with B4 C overlay.

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Figure 2

Test specimen. All dimensions in inches.

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Figure 3

Fatigue S-N curves for Hi-N/SiC-B4 C at 1200 °C in air. Tension-tension fatigue data from Ruggles-Wrenn [25].

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Figure 4

Typical evolution of stress-strain hysteresis response of Hi-N/SiC-B4 C composite with fatigue cycles at 1200 °C in air: (a) σmax  = 80 MPa, (b) σmax  = 200 MPa

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Figure 5

Maximum and minimum strains versus fatigue cycles for Hi-N/SiC-B4 C ceramic composite at 1200 °C in air

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Figure 6

Normalized modulus versus fatigue cycles for Hi-N/SiC-B4 C ceramic composite at 1200 °C in air

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Figure 7

Fracture surface of the specimen tested at 1200 °C (a) in tension-compression fatigue and (b) in tension-tension fatigue. Tension-tension fracture surface from Ruggles-Wrenn [25].

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Figure 8

Fracture surface of the specimen tested in tension-compression fatigue with σmax  = 160 MPa. SEM micrographs showing: (a) oxidation of fibers and matrix and (b) glassy phase in the oxidized region, (c) fiber pull-out and (d) no degradation of fiber-matrix interphase typical in the not oxidized region.

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Figure 9

Schematic showing matrix cracks developing in tension, compression, and tension-compression loading

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Figure 10

SEM micrograph showing matrix cracks oriented transverse to and parallel to the loading direction




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