Method for producing composite blade cleats for an aircraft turbine engine
AssigneeSafran
InventorsYann Didier Simon MARCHAL, Dominique Marie Christian COUPE, Damien Vincent LE CLOAREC
Life of this patent
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Abstract
Method for manufacturing composite blade cleats for an aircraft turbine engine, including providing a woven panel, including a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least a portion of the margin in common; injecting a matrix onto the panel; after injection, dividing the panel in order to separate the cleats from one another; machining the cleats to remove the margins.
Claims10
A method for manufacturing composite blade cleats for an aircraft turbine engine, comprising:
- providing a panel, the panel being woven and comprising a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least one portion of said margin in common;
- injecting a matrix onto the panel;
- after injection, dividing the panel in order to separate the cleats from one another;
- machining the cleats to removing the margins;
- wherein, after the injection, the cleats have a curved cross section, the curvature of a given cleat being reversed relative to the curvature of an adjacent cleat.
Dependencies are inferred from the claim text.