NDLI: Composite containment systems for jet engine fan blades

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Composite containment systems for jet engine fan blades

Content Provider	NASA Technical Reports Server (NTRS)
Author	Smith, G. T.
Copyright Year	1981
Description	The 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.
File Size	743904
Page Count	17
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810008958
Archival Resource Key	ark:/13960/t56f0p234
Language	English
Publisher Date	1981-01-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Ring Structures Structural Failure Weight Reduction Impact Tests Composite Structures Debris Kevlar Trademark Fan Blades Jet Engines Containment Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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