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Metal- matrix composite processing technologies for aircraft engine applications

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Abstract

Titanium metal-matrix composites (MMC) are prime candidate materials for aerospace applications be-cause of their excellent high-temperature longitudinal strength and stiffness and low density compared with nickel- and steel-base materials. This article examines the steps GE Aircraft Engines (GEAE) has taken to develop an induction plasma deposition (IPD) processing method for the fabrication of Ti6242/SiC MMC material. Information regarding process methodology, microstructures, and mechani-cal properties of consolidated MMC structures will be presented. The work presented was funded under the GE-Aircraft Engine IR & D program.

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References

  1. J.-M. Yang, S.M. Jeng, and C.J. Yang, Fracture Mechanisms of Fiber-Reinforced Titanium Alloy Matrix Composites, Part I: In- terfacial Behavior,Mater. Sci. Eng., Vol A138, 1991, p 155–167

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  5. P.K. Wright, “Creep Behavior and Modeling of Titanium/SCS-6 MMC,” Proc. Titanium Aluminide Composite Workshop, Or- lando, FL, Nov 1991

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Authors and Affiliations

  1. GE Aircraft Engines, 01910, Lynn, Massachusetts

    D. R. Pank & J. J. Jackson

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  1. D. R. Pank
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  2. J. J. Jackson
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Pank, D.R., Jackson, J.J. Metal- matrix composite processing technologies for aircraft engine applications. JMEP 2, 341–346 (1993). https://doi.org/10.1007/BF02648820

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  • DOI: https://doi.org/10.1007/BF02648820

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