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Composite containment systems for jet engine fan bladesThe use of composites in fan blade containment systems is investigated and the associated structural benefits of the composite system design are identified. Two basic types of containment structures were investigated. The short finned concept was evaluated using Kevlar/epoxy laminates for fins which were mounted in a 6061 T-6 aluminum ring. The long fin concept was evaluated with Kevlar/epoxy, 6Al4V titanium, and 2024 T-3 aluminum fins. The unfinned configurations consisted of the base-line steel sheet, a circumferentially oriented aluminum honeycomb, and a Kevlar cloth filled ring. Results obtained show that a substantial reduction in the fan blade containment system weight is possible. Minimization of damage within the engine arising from impact interaction between blade debris and the engine structure is also achieved.
Document ID
19810008958
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Smith, G. T. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Structural Mechanics
Report/Patent Number
E-700
NASA-TM-81675
Report Number: E-700
Report Number: NASA-TM-81675
Meeting Information
Meeting: Ann. Conf. of the Reinforced Plastics/Composites Inst. of the Soc. of the Plastics Ind., Inc.,
Location: Washington, DC
Country: United States
Start Date: February 16, 1981
End Date: February 20, 1981
Accession Number
81N17480
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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