摘要 |
<p>A hot section gas turbine engine component (10), comprising: a cured, reinforced, ceramic matrix composite portion (40,690) comprising a plurality of continuous tows extending substantially parallel to each other in a matrix; a discontinuously reinforced composite portion (650,680) 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 in a matrix material. The component having fine features such as thin edges with thicknesses of less than about 0.030 inches and small radii of less that about 0.030 inches formed using the combination of prepreg plies (40) layed up with non-ply ceramic inserts (650,680). The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert (650,680), resulting in fewer defects, such as wrinkles, and better dimensional control.</p> |