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Superhybrid composite blade impact studiesThe feasibility of superhybrid composite blades for meeting the mechanical design and impact resistance requirements of large fan blades for aircraft turbine engine applications was investigated. Two design concepts were evaluated: leading edge spar (TiCom) and center spar (TiCore), both with superhybrid composite shells. The investigation was both analytical and experimental. The results obtained show promise that superhybrid composites can be used to make light weight, high quality, large fan blades with good structural integrity. The blades tested successfully demonstrated their ability to meet steady state operating conditions, overspeed, and small bird impact requirements.
Document ID
19810002904
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chamis, C. C. (NASA Lewis Research Center Cleveland, OH, United States)
Lark, R. F. (NASA Lewis Research Center Cleveland, OH, United States)
Sinclair, J. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1980
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-81597
E-580
Report Number: NASA-TM-81597
Report Number: E-580
Meeting Information
Meeting: Ann. Intern. Gas Turbine Conf.
Location: Houston, TX
Country: United States
Start Date: March 9, 1981
End Date: March 12, 1981
Accession Number
81N11412
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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