Patent ID: 7549840
Filing Date: 2009-06-23
Classification: C04B,F01D,F05C,F05D,Y02T,Y10T

Abstract:
1. A method of manufacturing a turbine engine component comprising the steps of: providing a plurality of ceramic plies, each ply comprising woven ceramic fiber tows; providing a plurality of fugitive fibers tows; laying up the plurality of plies in a preselected arrangement to form a turbine engine component shape; inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that the fugitive fiber tows pass through at least two ceramic plies; burning off the fugitive fiber tows, the burning producing through-thickness void regions; 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, filling the through-thickness void regions with carbon-containing slurry; and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.