Patent ID: 7306826

Claim:
A method of manufacturing a rotatable turbine engine component, the component having a direction of maximum tensile stress during normal engine operation, comprising the steps of: providing a plurality of biased ceramic plies, each biased ply comprising ceramic fiber tows, the tows woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled; laying up the plurality of biased plies in a preselected arrangement to form a rotatable component shape, wherein a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of a preselected number of the plurality of biased plies lie about in the direction of maximum tensile stress during normal engine operation, wherein normal engine operation includes rotation of the rotatable turbine engine component; rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration; partially densifying the coated component preform using carbon-containing slurry; and further densifying the coated component preform with at least silicon to form a rotatable ceramic matrix composite aircraft engine component with biased architecture.