Composite blade with divergent root and method for making same

Details Composite blade with divergent root and method for making same Composite blade with divergent root and method for making same

1989-11-29

1991-09-17

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

416224, 2988971, 87 1, F01D 514

Patent

active

050490362

ABSTRACT:
A composite gas turbine engine blade is made by braiding a plurality of fibers to form a preform having an airfoil precursor portion and an integral root precursor portion. A plurality of fiber shaping inserts are positioned in the root precursor portion, either by braiding the root precursor portion around the inserts or inserting the fiber shaping inserts into the root precursor portion after braiding, 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 the composite blade with a dovetail shaped root.

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patent: 3737250 (1973-06-01), Pilpel et al.
patent: 3943020 (1976-03-01), Ashton
patent: 4460531 (1984-07-01), Harris et al.
patent: 4589176 (1986-05-01), Rosman et al.

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