Composite blade perform with divergent root

Details Composite blade perform with divergent root Composite blade perform with divergent root

1989-11-29

1991-05-07

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

416224, 2988971, F01D 514

Patent

active

050132164

ABSTRACT:
A braided gas turbine engine blade preform includes an airfoil precursor portion and an integral root precursor portion. A plurality of fiber shaping inserts are disposed in the root precursor portion, to impart an enlarged, divergent shape (e.g., dovetail precursor shape) to the braided root precursor portion. The braided preform with the enlarged, shaped root precursor portion is infiltrated with matrix material and shaped to near net shape to provide a composite blade with a dovetail shaped root.

REFERENCES:
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patent: 4696866 (1987-09-01), Tanaka et al.
patent: 4719837 (1988-01-01), McConnell et al.

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