Damage accumulation in titanium matrix composites under generic hypersonic vehicle flight simulation and sustained loads
- Georgia Inst. of Tech., Atlanta, GA (United States). School of Materials Science and Engineering
- General Electric Co., Schenectady, NY (United States). Power Generation System
- Galaxy Scientific Corp., Pleasantville, NJ (United States)
Titanium matrix composites (TMC), such as Ti-15V-3Cr-3Al-3Sn (Ti-15-3) reinforced with continuous silicon-carbide fibers (SCS-6), are being evaluated for use in hypersonic vehicles and advanced gas turbine engines where high strength-to-weight and high stiffness-to-weight ratios at elevated temperatures are critical. Such applications expose the composite to mechanical fatigue loading as well as thermally induced cycles. The damage accumulation behavior of a [0/90]2s laminate made of Ti-15V-3Cr-3Al-3Sn (Ti-15-3) reinforced with continuous silicon-carbide fibers (SCS-6) subjected to a simulated generic hypersonic flight profile, portions of the flight profile, and sustained loads was evaluated experimentally. Portions of the flight profile were used separately to isolate combinations of load and time at temperature that influenced the fatigue behavior of the composite. Sustained load tests were also conducted and the results were compared with the fatigue results under the flight profile and its portions. The test results indicated that the fatigue strength of this materials system is considerably reduced by a combination of load and time at temperature.
- OSTI ID:
- 531480
- Report Number(s):
- CONF-941159--; ISBN 0-8031-2001-X
- Country of Publication:
- United States
- Language:
- English
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