Patent ID: 7600979
Filing Date: 2009-10-13
Classification: B32B,C04B,F01D,F05C,F05D,Y02T,Y10T

Abstract:
1. A hot section gas turbine engine component, comprising: a cured, reinforced, ceramic matrix composite portion comprising a plurality of continuous tows extending substantially parallel to each other in a matrix; a discontinuously reinforced composite portion having substantially isotropic properties located at regions of contour changes and thickness changes of the component, the discontinuously reinforced composite portion comprising discontinuous fiber-including material selected from the group consisting of fiber, tow, and chopped pre-preg plies in a matrix material; wherein the discontinuously-reinforced composite portion is adjacent to the reinforced ceramic matrix composite portion comprising the plurality of continuous tows, and the discontinuously reinforced composite portion is cured to the reinforced ceramic matrix composite portion.