Patent ID: 6280550
Filing Date: 2001-08-28
Classification: B32B,C04B,F01D,Y02T,Y10T

Abstract:
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.