초록 ▼

A composite article is fabricated by preparing a porous first region piece having a first reinforcement material with no matrix, and rigidizing the first reinforcement material to form a porous first coated preform. At least one second-region layer of a second reinforcement material having no matrix

A composite article is fabricated by preparing a porous first region piece having a first reinforcement material with no matrix, and rigidizing the first reinforcement material to form a porous first coated preform. At least one second-region layer of a second reinforcement material having no matrix is applied in contact with at least a portion of the first coated preform. The second reinforcement material is rigidized, to form a second coated preform. A second-region matrix material is deposited into at least some of the porosity of the second coated preform. The reinforcement material may be silicon carbide fibers, and the infiltrated matrix may be silicon carbide.

대표청구항 ▼

[ What is claimed is:] [1.]1. A method for fabricating a composite article which is a portion of a gas turbine engine, comprising the steps of:preparing a porous first-region piece comprising a first reinforcement material having no matrix; thereafterrigidizing the first reinforcement material to fo

[ What is claimed is:] [1.]1. A method for fabricating a composite article which is a portion of a gas turbine engine, comprising the steps of:preparing a porous first-region piece comprising a first reinforcement material having no matrix; thereafterrigidizing the first reinforcement material to form a porous first coated preform; thereafterapplying at least one second-region layer of a second reinforcement material having no matrix in contact with at least a portion of the first coated preform; thereafterrigidizing the second reinforcement material, to form a second coated preform; and thereafterdepositing a second-region matrix material into at least some of the porosity of the second coated preform to produce the composite article of the second reinforcement material embedded in the second-region matrix material, wherein the composite article is a portion of a gas turbine engine.