Accession Number : ADA305240
Title : Fiber Composite Fan Blade Impact Improvement.
Descriptive Note : Final rept.,
Corporate Author : UNITED TECHNOLOGIES CORP WINDSOR LOCKS CT HAMILTON STANDARD DIV
Personal Author(s) : Graff, J. ; Stoltze, L. ; Varholak, E. M.
PDF Url : ADA305240
Report Date : FEB 1976
Pagination or Media Count : 88
Abstract : This report presents the results of a program conducted between July, 1974 and Nov. 1975 under NASA-Lewis Contract NAS3-17837. The objective of this program was to demonstrate the improved foreign object damage resistance of Hamilton Standard's metal matrix advanced composite fan blade which was developed beginning in 1973. The contract program included the fabrication, whirl impact test and subsequent evaluation of nine advanced composite fan blades of the "QCSEE' type design. The blades were designed to operate at a tip speed of 282 m/sec. (925 fps). The blade design was the spar/shell type, consisting of a titanium spar and boron/aluminum composite airfoils. The blade retention was designed to rock on impact with large birds, thereby reducing the blade bending stresses. The program demonstrated the ability of the blades to sustain Impacts with up to 681 g (24 oz) slices of birds at 0.38 rad with little damage (only 1.4% max weight loss) and 788 g (27.8 oz) slices of birds at 0.56 rad with only 3.2% max weight loss. Unbonding did not exceed 1.1% of the post-test blade area during any of the tests. Cne test using a fixed retention to preclude rocking confirmed improved FOD performance of the rocking retention. Correlation of the Hamilton Standard FOD analysis with the empirical results (strain gauge data in some tests) was very satisfactory, particularly in the prediction of gross loads. All blades in the post-test condition were judged capable of operation in accordance with the FAA guidelines for medium and large bird impacts. (MM)
Descriptors : *FIBER REINFORCED COMPOSITES, *METAL MATRIX COMPOSITES, *FAN BLADES, *AIRFOILS, *IMPACT STRENGTH, DAMAGE, IMPACT TESTS, DEFORMATION, COMPOSITE STRUCTURES, DEGREES OF FREEDOM, ICE, BONDED JOINTS, BIRD STRIKES, STRAIN GAGES, LEADING EDGES, BORON, FOREIGN OBJECT DAMAGE, WEIGHT REDUCTION, TITANIUM ALLOYS, BENDING STRESS, GELATINS, AERODYNAMIC CONTROL SURFACES.
Subject Categories : Aircraft
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE