Patent ID: 7282274
Filing Date: 2007-10-16
Classification: B32B,C04B,F05C,Y10T

Abstract:
1. An integral composite structural material for use in a gas turbine engine component comprising: an open metal structure having inner surfaces of metal defining a plurality of apertures and at least one external side, said metal structure being selected from the group consisting of aluminum, HSLA steel, stainless steel, carbon steel, nickel-based superalloys, iron-based superalloys and cobalt-based superalloys, said apertures having a geometry such that no dimension of said apertures is greater than about ¾ inch, wherein the total metal volume percent of the integral composite structure matrix, exclusive of ceramic matrix composite material, is in the range of about 10% to about 90%; ceramic matrix composite material laminated to the open metal structure so that the composite ceramic matrix material is disposed within a substantial portion of said apertures occupying a substantial volume of aperture space between the metal surfaces, said ceramic matrix composite material being bonded to a substantial portion of the at least one external side and said inner surfaces of said metal, said ceramic matrix composite comprising ceramic fibers and ceramic matrix material, said ceramic fibers being selected from the group consisting of alumina fiber, silica fiber, boric oxide fiber, silicon carbide fiber, glass fiber and combinations thereof, said ceramic matrix material being selected from the group consisting of zirconia, hafnia, alumina silicate, yttria, calcia aluminate, clay, and combinations thereof; and wherein the ceramic matrix composite material laminated to the open metal structure forms at least a portion of a gas turbine engine component.