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):

Report Date:

1976-02-01

Pagination or Media Count:

88.0

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 Standards 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 msec. 925 fps. The blade design was the sparshell type, consisting of a titanium spar and boronaluminum 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

Subject Categories:

  • Aircraft
  • Laminates and Composite Materials
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE