Patent ID: 7507466

Claim:
A ceramic matrix composite gas turbine engine component comprising: a plurality of cured ceramic matrix composite plies, each ply comprising ceramic fiber tows, each ceramic fiber tow comprising a plurality of ceramic fibers, the tows in each ply lying adjacent to one another such that each ply has a unidirectional orientation; a coating on the ceramic fibers, the coating selected from the group consisting of boron nitride, silicon nitride, silicon carbide, and combinations thereof; a ceramic matrix material lying in interstitial regions between the fibers and tows of each ply and the interstitial region between the plurality of plies; and at least a portion of the component comprising cured ceramic matrix composite plies, wherein each ceramic ply in at least the portion has a thickness in the range of about 0.005 inch to about 0.008 inch, inclusive of tows, coating, and interstitial ceramic matrix material, wherein the total thickness in at least the portion is no greater than about 0.021 inch.