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Cost/benefit assessment of the application of composite materials to subsonic commercial transport enginesResults from a number of studies concerned with the cost and benefits of applying advanced composite materials to commercial turbofan engines are summarized. For each application area the optimistic and pessimistic benefit projections were averaged to arrive at a projected yearly percentage fuel savings for a commercial fleet of advanced technology transport aircraft. Engine components included in the summary are the fan section which includes fan blades, fan frame/case, and the blade containment ring; the nacelle; and the high pressure turbine blades and vanes. The projected fuel savings resulting from the application of composites are 1.85 percent for the fan section, 1.75 percent for the nacelle, and 2.35 percent for the high pressure turbine.
Document ID
19770006121
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Faddoul, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Signorelli, R. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8996
NASA-TM-X-73557
Accession Number
77N13064
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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