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Advanced Aircraft Engine Microlaminated Intermetallic Composite Turbine Technology

Published online by Cambridge University Press:  10 February 2011

R. G. Rowe,
D. W. Skelly,
M. R. Jackson,
M. Larsen and
D. Lachapelle
R. G. Rowe
Affiliation:
GE Corporate Research and Development, Schenectady, NY 12309
D. W. Skelly
Affiliation:
GE Corporate Research and Development, Schenectady, NY 12309
M. R. Jackson
Affiliation:
GE Corporate Research and Development, Schenectady, NY 12309
M. Larsen
Affiliation:
GE Corporate Research and Development, Schenectady, NY 12309
D. Lachapelle
Affiliation:
GE Aircraft Engines, Cincinnati, OH 45215
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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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