Accession Number : ADA305110
Title : Metal Spar/Superhybrid Shell Composite Fan Blades.
Descriptive Note : Final rept.,
Corporate Author : GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP
Personal Author(s) : Salemme, C. T. ; Murphy, G. C.
PDF Url : ADA305110
Report Date : AUG 1979
Pagination or Media Count : 137
Abstract : This program was undertaken to establish the feasibility of using superhybrid materials for the manufacture and testing of large fan blades. In addition it was the objective of this program to investigate the FOD resistance of large metal spar/superhybrid fan blades. The technical effort reported herein was comprised of several elements of work, conducted in series. These elements included: (1) Preliminary blade design; (2) Detailed analysis of two selected superhybrid blade designs; (3) Manufacture of two process evaluation blades and destructive evaluation; and (4) Manufacture and whirligig testing of six prototype superhybrid blades. (AN)
Descriptors : *FAN BLADES, *GRAPHITE EPOXY COMPOSITES, MATHEMATICAL MODELS, STEADY STATE, MANUFACTURING, STRESS ANALYSIS, FINITE ELEMENT ANALYSIS, IMPACT TESTS, TENSILE STRESS, FABRICATION, EXTRUSION, COMPOSITE STRUCTURES, SHELLS(STRUCTURAL FORMS), CARBON CARBON COMPOSITES, FEASIBILITY STUDIES, SHEAR STRESSES, FLEXURAL STRENGTH, LIGHTWEIGHT, LEADING EDGES, QUALITY ASSURANCE, DESIGN CRITERIA, COMPRESSIVE STRENGTH, SKIN(STRUCTURAL), TITANIUM ALLOYS, RADIAL STRESS, HYBRIDIZATION, MOLDING TECHNIQUES, SPARS, BLADE TIPS, HIGH BYPASS TURBOFANS, STRUCTURAL INTEGRITY.
Subject Categories : Laminates and Composite Materials
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE