Method of making a composite blade with divergent root

Details Method of making a composite blade with divergent root Method of making a composite blade with divergent root

Filed on

1988-09-09

Date issued

1991-05-28

Examiner

Goldberg, Howard N.

Patent Class

Metal working

SubClass

Method of mechanical manufacture

SubSubClass

Impeller making

Other Related Categories

298897, 87 1, 264 81, 264103, 264273, 416219R, 416229A, 416241A, 416248, B21K 304

Type

Patent

Status

active

Patent number

050182714

Description

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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