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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Isothermal Fatigue Behavior and Damage Modeling of a High Temperature Woven PMC

[+] Author and Article Information
A. L. Gyekenyesi

NASA Glenn Research Center, MS 6-1, 21000 Brookpark Road, Cleveland, OH 44135

J. Eng. Gas Turbines Power 122(1), 62-68 (Oct 20, 1999) (7 pages) doi:10.1115/1.483176 History: Received February 25, 1998; Revised October 20, 1999
Copyright © 2000 by ASME
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References

Bowles, K. J., Roberts, G. D., and Kamvouris, J. E., 1996, “Long Term Isothermal Aging Effects on Carbon Fabric Reinforced PMR-15 Composites: Compression Strength,” NASA TM-107129.
Gyekenyesi, A. L., 1998, “Isothermal Fatigue, Damage Accumulation, and Life Prediction of a Woven PMC,” NASA CR-206593.
Wang,  S. S., and Chim,  E. S. M., 1983, “Fatigue Damage and Degradation in Random Short-Fiber SMC Composites,” J. Compos. Mater., 17, p. 114.
Poursartip, A., Ashby, M. F., and Beaumont, P. W. R., 1982, “Damage Accumulation During Fatigue of Composites,” Proceedings, International Conference on Composite Materials IV, Tokyo.
Liu, B. Y., 1992, “Fatigue and Damage Tolerance Analysis of Composite Laminates: Stiffness Loss, Damage Modeling, and Life Predictions,” Master’s thesis, Dept. of Mech. Engineering, McGill University, Montreal, Quebec, Canada.
Ye,  L., 1989, “On Fatigue Damage Accumulation and Material Degradation in Composite Materials,” Compos. Sci. Technol., 36, pp. 339–350.
Lemaitre, J., and Chaboche, J. L., 1990, Mechanics of Solid Materials, Cambridge University Press, New York.
Hwang, W., and Han, K. S., 1989, “Fatigue of Composite Materials: Damage Model and Life Prediction,” Composite Materials: Fatigue and Fracture, Second Volume, ASTM STP 1012, P. A. Lagace, ed., American Society for Testing and Materials, Philadelphia, PA, pp. 87–102.

Figures

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Model versus data comparison of normalized compressive modulus as a function of cycles at 204°C (400°F)
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Residual compressive strength behavior as a function of damage (i.e., current compressive modulus)
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Normalized compressive modulus at various maximum stresses for RT condition. Each line is an average of three specimens.
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Comparison of normalized compressive modulus degradation behavior between RT and ET at an equivalent stress
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Normalized compressive modulus degradation behavior for multiple specimens at 316°C (600°F): σmax=310 MPa (45 ksi).
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Normalized compressive modulus degradation behavior for multiple specimens at 22°C (72°F): σmax=379 MPa (55 ksi).
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Stress based isothermal fatigue life for T650-35/PMR15 (0/90) weave
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Microscopic edge view of transverse cracks in a typical RT tensile specimen after loading to 758 MPa (110 ksi)
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Illustration of microscopic damage in a (0/90) weave: edge view
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Schematic of specimen geometry

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