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Advanced Aircraft Engine Microlaminated Intermetallic Composite Turbine Technology

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Abstract

Higher gas path temperatures for greater aircraft engine thrust and efficiency will require both higher temperature gas turbine airfoil materials and optimization of internal cooling technology. Microlaminated composites consisting of very high temperature intermetallic compounds and ductile refractory metals offer a means of achieving higher temperature turbine airfoil capability without sacrificing low temperature fracture resistance. Physical vapor deposition, used to synthesize microlaminated composites, also offers a means of fabricating advanced turbine blade internal cooling designs. The low temperature fracture resistance of microlaminated Nb(Cr)-Cr2Nb microlaminated composites approached 20 MPa√m in fracture resistance curves, but the fine grain size of vapor deposited intermetallics indicates a need to develop creep resistant microstructures.

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Authors and Affiliations

  1. GE Corporate Research and Development, Schenectady, NY, 12309, USA

    R. G. Rowe, D. W. Skelly, M. R. Jackson & M. Larsen

  2. GE Aircraft Engines, Cincinnati, OH, 45215, USA

    D. Lachapelle

Authors
  1. R. G. Rowe
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  2. D. W. Skelly
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  3. M. R. Jackson
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  4. M. Larsen
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  5. D. Lachapelle
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Rowe, R.G., Skelly, D.W., Jackson, M.R. et al. Advanced Aircraft Engine Microlaminated Intermetallic Composite Turbine Technology. MRS Online Proceedings Library 434, 3–13 (1996). https://doi.org/10.1557/PROC-434-3

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  • DOI: https://doi.org/10.1557/PROC-434-3

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